NREL's S813 Airfoil (s813-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S813 Airfoil (s813-nr) Reynolds number: 1,000,000 Max Cl/Cd: 130.81 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s813-nr-1000000.txt Download as CSV file: xf-s813-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S813 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.7248 0.09495 0.09275 -0.0668 1.0000 0.0068
-16.750 -0.7547 0.08522 0.08287 -0.0722 1.0000 0.0068
-16.500 -0.7920 0.07473 0.07212 -0.0780 1.0000 0.0066
-16.250 -0.8056 0.06877 0.06607 -0.0815 1.0000 0.0067
-16.000 -0.8048 0.06527 0.06254 -0.0836 1.0000 0.0069
-15.750 -0.8280 0.05849 0.05556 -0.0869 1.0000 0.0068
-15.500 -0.8366 0.05418 0.05114 -0.0889 1.0000 0.0068
-15.250 -0.8546 0.04908 0.04586 -0.0905 1.0000 0.0068
-15.000 -0.8586 0.04603 0.04272 -0.0913 1.0000 0.0069
-14.750 -0.8505 0.04408 0.04076 -0.0923 0.9878 0.0071
-14.500 -0.8222 0.04067 0.03720 -0.0999 0.9693 0.0073
-14.250 -0.7870 0.03770 0.03402 -0.1080 0.9364 0.0075
-14.000 -0.7914 0.03497 0.03082 -0.1078 0.8678 0.0075
-13.750 -0.7877 0.03370 0.02938 -0.1067 0.8437 0.0077
-13.500 -0.7881 0.03187 0.02736 -0.1055 0.8296 0.0078
-13.250 -0.7837 0.03044 0.02579 -0.1045 0.8196 0.0080
-13.000 -0.7795 0.02898 0.02418 -0.1033 0.8111 0.0080
-12.750 -0.7724 0.02775 0.02282 -0.1023 0.8044 0.0082
-12.500 -0.7627 0.02677 0.02174 -0.1013 0.7983 0.0085
-12.250 -0.7551 0.02558 0.02041 -0.1000 0.7929 0.0086
-12.000 -0.7430 0.02476 0.01951 -0.0991 0.7884 0.0087
-11.750 -0.7354 0.02350 0.01812 -0.0976 0.7841 0.0089
-11.500 -0.7337 0.02180 0.01627 -0.0954 0.7799 0.0092
-11.250 -0.7231 0.02089 0.01530 -0.0940 0.7764 0.0095
-11.000 -0.7063 0.02048 0.01489 -0.0933 0.7732 0.0101
-10.750 -0.6944 0.01964 0.01398 -0.0919 0.7700 0.0102
-10.500 -0.6803 0.01902 0.01328 -0.0906 0.7669 0.0106
-10.250 -0.6657 0.01846 0.01265 -0.0893 0.7635 0.0110
-10.000 -0.6484 0.01806 0.01221 -0.0883 0.7611 0.0115
-9.750 -0.6322 0.01761 0.01171 -0.0870 0.7585 0.0118
-9.500 -0.6169 0.01716 0.01119 -0.0855 0.7559 0.0120
-9.250 -0.6134 0.01613 0.01006 -0.0821 0.7533 0.0126
-9.000 -0.5994 0.01547 0.00935 -0.0804 0.7509 0.0133
-8.750 -0.5799 0.01510 0.00894 -0.0795 0.7483 0.0140
-8.500 -0.5604 0.01463 0.00844 -0.0786 0.7467 0.0145
-8.250 -0.5395 0.01422 0.00799 -0.0778 0.7448 0.0152
-8.000 -0.5170 0.01390 0.00763 -0.0773 0.7429 0.0159
-7.750 -0.4943 0.01358 0.00727 -0.0768 0.7409 0.0164
-7.500 -0.4775 0.01282 0.00643 -0.0754 0.7390 0.0177
-7.250 -0.4548 0.01246 0.00603 -0.0749 0.7370 0.0187
-7.000 -0.4312 0.01215 0.00567 -0.0745 0.7350 0.0197
-6.750 -0.4070 0.01188 0.00535 -0.0742 0.7331 0.0206
-6.500 -0.3819 0.01162 0.00507 -0.0741 0.7318 0.0213
-6.250 -0.3582 0.01123 0.00464 -0.0737 0.7303 0.0235
-6.000 -0.3332 0.01094 0.00434 -0.0735 0.7287 0.0256
-5.750 -0.3074 0.01071 0.00409 -0.0734 0.7271 0.0279
-5.500 -0.2840 0.01025 0.00376 -0.0730 0.7255 0.0498
-5.250 -0.2619 0.00968 0.00342 -0.0725 0.7240 0.1002
-5.000 -0.2380 0.00924 0.00317 -0.0723 0.7224 0.1461
-4.500 -0.1893 0.00844 0.00275 -0.0721 0.7188 0.2534
-4.250 -0.1644 0.00802 0.00256 -0.0720 0.7176 0.3142
-4.000 -0.1399 0.00754 0.00236 -0.0720 0.7164 0.3882
-3.750 -0.1144 0.00712 0.00218 -0.0720 0.7151 0.4555
-3.500 -0.0880 0.00681 0.00206 -0.0721 0.7138 0.5124
-3.250 -0.0609 0.00658 0.00199 -0.0723 0.7124 0.5617
-3.000 -0.0331 0.00646 0.00198 -0.0725 0.7110 0.6065
-2.750 -0.0045 0.00645 0.00202 -0.0728 0.7096 0.6357
-2.500 0.0247 0.00647 0.00203 -0.0732 0.7082 0.6482
-2.250 0.0541 0.00652 0.00203 -0.0737 0.7069 0.6575
-2.000 0.0833 0.00656 0.00207 -0.0741 0.7055 0.6651
-1.750 0.1128 0.00666 0.00212 -0.0746 0.7040 0.6718
-1.500 0.1420 0.00668 0.00214 -0.0751 0.7029 0.6769
-1.250 0.1713 0.00671 0.00218 -0.0755 0.7019 0.6820
-1.000 0.2006 0.00675 0.00220 -0.0760 0.7006 0.6869
-0.750 0.2299 0.00676 0.00222 -0.0764 0.6992 0.6911
-0.500 0.2591 0.00678 0.00225 -0.0769 0.6978 0.6949
-0.250 0.2884 0.00682 0.00229 -0.0773 0.6965 0.6989
0.000 0.3178 0.00687 0.00232 -0.0778 0.6953 0.7027
0.250 0.3472 0.00689 0.00234 -0.0783 0.6940 0.7060
0.500 0.3764 0.00691 0.00238 -0.0788 0.6927 0.7091
0.750 0.4057 0.00696 0.00243 -0.0793 0.6914 0.7122
1.000 0.4351 0.00704 0.00250 -0.0798 0.6900 0.7154
1.250 0.4645 0.00714 0.00259 -0.0803 0.6886 0.7183
1.500 0.4935 0.00713 0.00262 -0.0808 0.6875 0.7211
1.750 0.5223 0.00714 0.00268 -0.0812 0.6861 0.7237
2.000 0.5513 0.00717 0.00274 -0.0816 0.6846 0.7261
2.250 0.5803 0.00717 0.00277 -0.0820 0.6824 0.7286
2.500 0.6092 0.00713 0.00273 -0.0824 0.6788 0.7309
2.750 0.6380 0.00714 0.00270 -0.0827 0.6736 0.7330
3.000 0.6657 0.00704 0.00264 -0.0828 0.6681 0.7348
3.250 0.6938 0.00695 0.00258 -0.0829 0.6629 0.7371
3.500 0.7219 0.00695 0.00260 -0.0832 0.6581 0.7390
3.750 0.7498 0.00692 0.00263 -0.0833 0.6531 0.7410
4.000 0.7776 0.00690 0.00262 -0.0835 0.6473 0.7431
4.250 0.8054 0.00691 0.00266 -0.0836 0.6414 0.7451
4.500 0.8328 0.00690 0.00269 -0.0837 0.6334 0.7471
4.750 0.8598 0.00692 0.00272 -0.0837 0.6223 0.7489
5.000 0.8865 0.00694 0.00277 -0.0837 0.6119 0.7510
5.250 0.9124 0.00699 0.00283 -0.0835 0.5978 0.7531
5.500 0.9353 0.00715 0.00294 -0.0827 0.5695 0.7551
5.750 0.9470 0.00774 0.00324 -0.0798 0.5015 0.7575
6.000 0.9500 0.00870 0.00381 -0.0754 0.4209 0.7603
6.250 0.9518 0.00960 0.00438 -0.0709 0.3529 0.7629
6.500 0.9513 0.01031 0.00485 -0.0658 0.3003 0.7655
6.750 0.9493 0.01107 0.00542 -0.0606 0.2541 0.7686
7.000 0.9517 0.01183 0.00602 -0.0565 0.2160 0.7716
7.250 0.9549 0.01263 0.00667 -0.0527 0.1811 0.7749
7.750 0.9643 0.01436 0.00811 -0.0461 0.1203 0.7814
8.000 0.9735 0.01511 0.00880 -0.0438 0.1005 0.7848
8.250 0.9824 0.01595 0.00955 -0.0414 0.0822 0.7884
8.500 0.9937 0.01672 0.01028 -0.0396 0.0685 0.7921
8.750 1.0051 0.01752 0.01102 -0.0378 0.0563 0.7959
9.000 1.0176 0.01826 0.01176 -0.0361 0.0485 0.8002
9.250 1.0321 0.01893 0.01245 -0.0348 0.0433 0.8050
9.500 1.0452 0.01972 0.01322 -0.0334 0.0381 0.8097
9.750 1.0603 0.02036 0.01392 -0.0322 0.0351 0.8149
10.000 1.0744 0.02109 0.01468 -0.0309 0.0323 0.8209
10.250 1.0866 0.02195 0.01557 -0.0294 0.0285 0.8274
10.500 1.1027 0.02256 0.01625 -0.0285 0.0271 0.8354
10.750 1.1164 0.02332 0.01704 -0.0273 0.0245 0.8446
11.000 1.1281 0.02419 0.01797 -0.0258 0.0216 0.8568
11.250 1.1422 0.02485 0.01873 -0.0246 0.0195 0.8752
11.500 1.1515 0.02561 0.01965 -0.0226 0.0166 0.9329
11.750 1.1734 0.02659 0.02068 -0.0236 0.0138 1.0000
12.000 1.1847 0.02770 0.02180 -0.0225 0.0110 1.0000
12.250 1.1947 0.02893 0.02303 -0.0213 0.0095 1.0000
12.500 1.2077 0.02996 0.02411 -0.0204 0.0092 1.0000
12.750 1.2200 0.03106 0.02525 -0.0195 0.0085 1.0000
13.000 1.2306 0.03231 0.02653 -0.0185 0.0078 1.0000
13.250 1.2409 0.03361 0.02787 -0.0175 0.0075 1.0000
13.500 1.2452 0.03543 0.02978 -0.0161 0.0069 1.0000
13.750 1.2574 0.03663 0.03104 -0.0154 0.0067 1.0000
14.000 1.2667 0.03809 0.03257 -0.0145 0.0066 1.0000
14.250 1.2769 0.03950 0.03404 -0.0138 0.0064 1.0000
14.500 1.2868 0.04097 0.03557 -0.0131 0.0062 1.0000
14.750 1.2943 0.04269 0.03736 -0.0124 0.0060 1.0000
15.000 1.3030 0.04432 0.03905 -0.0118 0.0057 1.0000
15.250 1.3108 0.04608 0.04086 -0.0112 0.0054 1.0000
15.500 1.3173 0.04799 0.04285 -0.0107 0.0054 1.0000
15.750 1.3205 0.05030 0.04524 -0.0101 0.0052 1.0000
16.000 1.3249 0.05254 0.04757 -0.0097 0.0052 1.0000
16.250 1.3240 0.05540 0.05053 -0.0092 0.0050 1.0000
16.500 1.3182 0.05893 0.05419 -0.0088 0.0048 1.0000
16.750 1.3197 0.06173 0.05709 -0.0088 0.0048 1.0000
17.000 1.3094 0.06604 0.06154 -0.0087 0.0047 1.0000
17.250 1.3027 0.07007 0.06572 -0.0090 0.0046 1.0000
17.500 1.3054 0.07303 0.06876 -0.0096 0.0046 1.0000
17.750 1.3021 0.07688 0.07274 -0.0103 0.0045 1.0000
18.000 1.2999 0.08068 0.07664 -0.0112 0.0045 1.0000
18.250 1.2946 0.08502 0.08110 -0.0124 0.0045 1.0000
18.500 1.2881 0.08972 0.08593 -0.0139 0.0045 1.0000
18.750 1.2832 0.09431 0.09064 -0.0156 0.0044 1.0000
19.000 1.2769 0.09923 0.09568 -0.0175 0.0044 1.0000
19.250 1.2678 0.10477 0.10136 -0.0199 0.0044 1.0000
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