S8037 (16%) (s8037-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8037 (16%) (s8037-il) Reynolds number: 500,000 Max Cl/Cd: 85.29 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8037-il-500000-n5.txt Download as CSV file: xf-s8037-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8037 (16%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7438 0.08803 0.08474 -0.0567 1.0000 0.0081
-16.000 -0.7773 0.07777 0.07426 -0.0627 1.0000 0.0081
-15.750 -0.7986 0.07025 0.06658 -0.0671 1.0000 0.0081
-15.500 -0.8282 0.06208 0.05817 -0.0716 1.0000 0.0080
-15.250 -0.8383 0.05734 0.05333 -0.0742 1.0000 0.0081
-15.000 -0.8427 0.05370 0.04962 -0.0759 1.0000 0.0082
-14.750 -0.8563 0.04917 0.04494 -0.0776 1.0000 0.0082
-14.500 -0.8655 0.04547 0.04109 -0.0786 1.0000 0.0082
-14.250 -0.8688 0.04269 0.03822 -0.0790 1.0000 0.0083
-14.000 -0.8718 0.04014 0.03558 -0.0789 1.0000 0.0084
-13.750 -0.8733 0.03792 0.03327 -0.0785 1.0000 0.0085
-13.500 -0.8776 0.03559 0.03081 -0.0775 1.0000 0.0085
-13.250 -0.8780 0.03379 0.02892 -0.0762 1.0000 0.0085
-13.000 -0.8767 0.03230 0.02735 -0.0747 1.0000 0.0088
-12.750 -0.8778 0.03072 0.02567 -0.0725 1.0000 0.0088
-12.500 -0.8767 0.02948 0.02434 -0.0702 1.0000 0.0089
-12.000 -0.8451 0.02672 0.02135 -0.0704 0.9887 0.0094
-11.750 -0.8327 0.02545 0.01996 -0.0694 0.9608 0.0095
-11.500 -0.7936 0.02398 0.01832 -0.0736 0.9431 0.0098
-11.000 -0.6931 0.02105 0.01506 -0.0865 0.9081 0.0105
-10.750 -0.6586 0.02020 0.01403 -0.0892 0.8769 0.0109
-10.500 -0.6419 0.01964 0.01331 -0.0878 0.8509 0.0112
-10.250 -0.6289 0.01912 0.01265 -0.0856 0.8320 0.0114
-10.000 -0.6158 0.01864 0.01204 -0.0833 0.8169 0.0118
-9.750 -0.6019 0.01820 0.01148 -0.0810 0.8039 0.0122
-9.500 -0.5865 0.01784 0.01098 -0.0789 0.7930 0.0126
-9.250 -0.5747 0.01731 0.01038 -0.0762 0.7830 0.0130
-9.000 -0.5618 0.01686 0.00985 -0.0736 0.7748 0.0133
-8.750 -0.5459 0.01647 0.00940 -0.0716 0.7665 0.0137
-8.500 -0.5285 0.01608 0.00894 -0.0698 0.7593 0.0143
-8.250 -0.5101 0.01571 0.00850 -0.0682 0.7521 0.0147
-8.000 -0.4915 0.01535 0.00806 -0.0665 0.7458 0.0151
-7.750 -0.4722 0.01499 0.00763 -0.0650 0.7398 0.0158
-7.500 -0.4533 0.01459 0.00719 -0.0634 0.7337 0.0164
-7.250 -0.4331 0.01428 0.00682 -0.0621 0.7280 0.0173
-7.000 -0.4117 0.01400 0.00649 -0.0609 0.7227 0.0182
-6.750 -0.3906 0.01370 0.00614 -0.0596 0.7172 0.0191
-6.500 -0.3698 0.01339 0.00579 -0.0583 0.7119 0.0203
-6.250 -0.3479 0.01312 0.00548 -0.0572 0.7071 0.0217
-6.000 -0.3257 0.01286 0.00518 -0.0561 0.7019 0.0234
-5.750 -0.3036 0.01261 0.00491 -0.0550 0.6969 0.0262
-5.500 -0.2814 0.01236 0.00464 -0.0539 0.6924 0.0302
-5.250 -0.2588 0.01210 0.00439 -0.0529 0.6877 0.0366
-5.000 -0.2362 0.01185 0.00417 -0.0519 0.6829 0.0457
-4.750 -0.2138 0.01160 0.00395 -0.0509 0.6785 0.0585
-4.250 -0.1682 0.01112 0.00357 -0.0490 0.6695 0.0905
-4.000 -0.1453 0.01089 0.00339 -0.0480 0.6649 0.1119
-3.750 -0.1231 0.01064 0.00321 -0.0470 0.6607 0.1400
-3.500 -0.1015 0.01030 0.00304 -0.0458 0.6565 0.1810
-3.250 -0.0825 0.00983 0.00285 -0.0443 0.6517 0.2524
-2.750 -0.0452 0.00898 0.00253 -0.0408 0.6428 0.4066
-2.500 -0.0237 0.00872 0.00245 -0.0396 0.6381 0.4576
-2.250 -0.0015 0.00854 0.00238 -0.0384 0.6330 0.5001
-2.000 0.0213 0.00842 0.00233 -0.0373 0.6282 0.5356
-1.750 0.0446 0.00831 0.00230 -0.0362 0.6235 0.5691
-1.500 0.0684 0.00823 0.00228 -0.0353 0.6184 0.5961
-1.250 0.0930 0.00819 0.00225 -0.0345 0.6132 0.6151
-1.000 0.1175 0.00815 0.00223 -0.0338 0.6086 0.6360
-0.750 0.1418 0.00809 0.00223 -0.0329 0.6032 0.6578
-0.500 0.1665 0.00807 0.00221 -0.0322 0.5979 0.6745
-0.250 0.1917 0.00807 0.00220 -0.0316 0.5931 0.6880
0.000 0.2172 0.00804 0.00221 -0.0310 0.5877 0.7006
0.250 0.2425 0.00804 0.00221 -0.0304 0.5820 0.7126
0.750 0.2932 0.00804 0.00222 -0.0293 0.5701 0.7353
1.000 0.3181 0.00806 0.00223 -0.0286 0.5637 0.7466
1.500 0.3684 0.00807 0.00229 -0.0274 0.5509 0.7722
1.750 0.3931 0.00810 0.00232 -0.0267 0.5447 0.7860
2.000 0.4185 0.00810 0.00237 -0.0261 0.5373 0.7996
2.250 0.4429 0.00814 0.00241 -0.0254 0.5299 0.8143
2.500 0.4690 0.00815 0.00247 -0.0250 0.5222 0.8297
2.750 0.4948 0.00821 0.00254 -0.0246 0.5141 0.8467
3.000 0.5240 0.00824 0.00262 -0.0249 0.5057 0.8643
3.250 0.5566 0.00833 0.00274 -0.0260 0.4970 0.8822
3.500 0.5957 0.00845 0.00288 -0.0286 0.4869 0.8982
3.750 0.6393 0.00862 0.00304 -0.0322 0.4757 0.9107
4.000 0.6845 0.00883 0.00321 -0.0362 0.4629 0.9192
4.250 0.7251 0.00905 0.00339 -0.0392 0.4494 0.9282
4.500 0.7638 0.00928 0.00360 -0.0417 0.4359 0.9348
4.750 0.7957 0.00952 0.00380 -0.0428 0.4220 0.9437
5.000 0.8279 0.00977 0.00402 -0.0439 0.4084 0.9502
5.500 0.8795 0.01034 0.00448 -0.0436 0.3791 0.9691
5.750 0.9066 0.01063 0.00473 -0.0437 0.3653 0.9763
6.250 0.9622 0.01133 0.00529 -0.0445 0.3313 0.9873
6.500 0.9907 0.01174 0.00562 -0.0452 0.3112 0.9917
7.000 1.0507 0.01255 0.00627 -0.0474 0.2754 0.9981
7.250 1.0768 0.01294 0.00660 -0.0476 0.2604 1.0000
7.500 1.0874 0.01325 0.00688 -0.0445 0.2493 1.0000
7.750 1.0970 0.01356 0.00717 -0.0412 0.2400 1.0000
8.250 1.1065 0.01419 0.00775 -0.0327 0.2216 1.0000
8.500 1.1123 0.01457 0.00810 -0.0288 0.2126 1.0000
8.750 1.1202 0.01497 0.00849 -0.0254 0.2038 1.0000
9.000 1.1283 0.01541 0.00892 -0.0222 0.1955 1.0000
9.250 1.1353 0.01595 0.00943 -0.0189 0.1862 1.0000
9.500 1.1449 0.01646 0.00994 -0.0162 0.1780 1.0000
9.750 1.1524 0.01711 0.01056 -0.0134 0.1694 1.0000
10.000 1.1621 0.01773 0.01119 -0.0110 0.1618 1.0000
10.250 1.1702 0.01848 0.01192 -0.0086 0.1538 1.0000
10.500 1.1798 0.01922 0.01267 -0.0065 0.1468 1.0000
10.750 1.1884 0.02008 0.01352 -0.0044 0.1400 1.0000
11.000 1.1983 0.02091 0.01437 -0.0026 0.1340 1.0000
11.250 1.2063 0.02192 0.01538 -0.0008 0.1279 1.0000
11.500 1.2165 0.02283 0.01632 0.0008 0.1221 1.0000
11.750 1.2240 0.02397 0.01744 0.0024 0.1161 1.0000
12.000 1.2338 0.02499 0.01850 0.0038 0.1112 1.0000
12.250 1.2420 0.02616 0.01969 0.0052 0.1060 1.0000
12.500 1.2497 0.02740 0.02095 0.0065 0.1016 1.0000
12.750 1.2586 0.02859 0.02218 0.0076 0.0974 1.0000
13.000 1.2652 0.02998 0.02358 0.0089 0.0928 1.0000
13.250 1.2723 0.03136 0.02500 0.0100 0.0886 1.0000
13.500 1.2792 0.03280 0.02646 0.0110 0.0844 1.0000
13.750 1.2839 0.03443 0.02812 0.0121 0.0806 1.0000
14.000 1.2903 0.03598 0.02971 0.0129 0.0778 1.0000
14.250 1.2969 0.03754 0.03132 0.0138 0.0748 1.0000
14.500 1.3005 0.03940 0.03321 0.0146 0.0712 1.0000
14.750 1.3040 0.04133 0.03518 0.0153 0.0685 1.0000
15.000 1.3103 0.04305 0.03696 0.0158 0.0662 1.0000
15.250 1.3146 0.04498 0.03895 0.0164 0.0635 1.0000
15.500 1.3169 0.04717 0.04119 0.0168 0.0610 1.0000
15.750 1.3185 0.04948 0.04354 0.0172 0.0586 1.0000
16.000 1.3231 0.05153 0.04566 0.0175 0.0564 1.0000
16.250 1.3254 0.05384 0.04803 0.0177 0.0541 1.0000
16.500 1.3255 0.05645 0.05069 0.0178 0.0520 1.0000
16.750 1.3250 0.05917 0.05346 0.0178 0.0500 1.0000
17.000 1.3276 0.06160 0.05596 0.0178 0.0481 1.0000
17.250 1.3277 0.06435 0.05878 0.0176 0.0464 1.0000
17.500 1.3247 0.06752 0.06200 0.0173 0.0442 1.0000
17.750 1.3220 0.07070 0.06524 0.0170 0.0424 1.0000
18.000 1.3219 0.07362 0.06824 0.0166 0.0414 1.0000
18.250 1.3199 0.07681 0.07151 0.0160 0.0395 1.0000
18.500 1.3156 0.08034 0.07510 0.0154 0.0379 1.0000
18.750 1.3097 0.08414 0.07896 0.0145 0.0366 1.0000
19.000 1.3051 0.08783 0.08274 0.0137 0.0357 1.0000
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Polar data table (+)
Polar graphs
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