RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.58 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5213-il-1000000-n5.txt Download as CSV file: xf-rae5213-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE(NPL) 5213 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -1.0513 0.06321 0.06051 -0.0448 1.0000 0.0062
-15.250 -1.0889 0.05275 0.04981 -0.0525 1.0000 0.0062
-15.000 -1.1132 0.04595 0.04281 -0.0569 1.0000 0.0061
-14.750 -1.1233 0.04166 0.03838 -0.0592 1.0000 0.0062
-14.500 -1.1326 0.03781 0.03437 -0.0609 1.0000 0.0062
-14.250 -1.1379 0.03470 0.03112 -0.0618 1.0000 0.0061
-14.000 -1.1402 0.03212 0.02841 -0.0622 1.0000 0.0062
-13.750 -1.1412 0.03001 0.02619 -0.0620 1.0000 0.0063
-13.500 -1.1443 0.02829 0.02435 -0.0604 1.0000 0.0063
-13.250 -1.1378 0.02688 0.02281 -0.0591 1.0000 0.0063
-13.000 -1.1271 0.02557 0.02139 -0.0581 1.0000 0.0064
-12.750 -1.1139 0.02439 0.02009 -0.0571 1.0000 0.0065
-12.500 -1.0990 0.02330 0.01890 -0.0562 1.0000 0.0065
-12.250 -1.0826 0.02230 0.01780 -0.0553 1.0000 0.0066
-12.000 -1.0653 0.02136 0.01676 -0.0544 1.0000 0.0067
-11.750 -1.0470 0.02050 0.01580 -0.0535 1.0000 0.0068
-11.500 -1.0282 0.01967 0.01489 -0.0526 1.0000 0.0069
-11.250 -1.0086 0.01894 0.01407 -0.0517 1.0000 0.0070
-11.000 -0.9886 0.01822 0.01328 -0.0508 1.0000 0.0070
-10.750 -0.9682 0.01758 0.01256 -0.0499 1.0000 0.0072
-10.500 -0.9479 0.01690 0.01181 -0.0489 1.0000 0.0073
-10.250 -0.9276 0.01623 0.01109 -0.0479 1.0000 0.0075
-10.000 -0.9066 0.01568 0.01050 -0.0469 1.0000 0.0077
-9.750 -0.8834 0.01517 0.00995 -0.0464 0.9997 0.0079
-9.500 -0.8528 0.01466 0.00940 -0.0474 0.9982 0.0082
-9.250 -0.8221 0.01417 0.00887 -0.0483 0.9963 0.0085
-9.000 -0.7910 0.01369 0.00834 -0.0493 0.9944 0.0088
-8.750 -0.7613 0.01323 0.00783 -0.0500 0.9920 0.0091
-8.500 -0.7307 0.01279 0.00735 -0.0508 0.9897 0.0094
-8.250 -0.6994 0.01237 0.00692 -0.0517 0.9876 0.0098
-8.000 -0.6671 0.01202 0.00656 -0.0529 0.9860 0.0103
-7.750 -0.6351 0.01169 0.00622 -0.0539 0.9840 0.0108
-7.500 -0.6056 0.01135 0.00586 -0.0544 0.9800 0.0113
-7.250 -0.5742 0.01102 0.00551 -0.0552 0.9766 0.0118
-7.000 -0.5424 0.01074 0.00522 -0.0561 0.9734 0.0123
-6.750 -0.5140 0.01049 0.00497 -0.0563 0.9667 0.0130
-6.500 -0.4834 0.01022 0.00468 -0.0569 0.9609 0.0136
-6.250 -0.4540 0.00998 0.00440 -0.0572 0.9536 0.0142
-6.000 -0.4245 0.00972 0.00414 -0.0575 0.9465 0.0149
-5.750 -0.3960 0.00951 0.00391 -0.0576 0.9374 0.0156
-5.500 -0.3680 0.00931 0.00369 -0.0575 0.9279 0.0164
-5.250 -0.3404 0.00914 0.00347 -0.0574 0.9175 0.0169
-5.000 -0.3132 0.00892 0.00323 -0.0571 0.9064 0.0178
-4.750 -0.2859 0.00876 0.00304 -0.0569 0.8961 0.0186
-4.500 -0.2585 0.00862 0.00287 -0.0567 0.8857 0.0196
-4.250 -0.2311 0.00845 0.00266 -0.0565 0.8755 0.0205
-4.000 -0.2039 0.00830 0.00248 -0.0562 0.8651 0.0217
-3.750 -0.1763 0.00815 0.00232 -0.0561 0.8545 0.0227
-3.500 -0.1487 0.00803 0.00215 -0.0559 0.8433 0.0235
-3.000 -0.0939 0.00779 0.00184 -0.0554 0.8157 0.0266
-2.750 -0.0663 0.00768 0.00171 -0.0552 0.8024 0.0292
-2.500 -0.0389 0.00759 0.00159 -0.0549 0.7869 0.0347
-2.250 -0.0117 0.00747 0.00148 -0.0547 0.7692 0.0494
-2.000 0.0157 0.00736 0.00138 -0.0545 0.7538 0.0676
-1.750 0.0432 0.00717 0.00128 -0.0543 0.7410 0.1054
-1.500 0.0706 0.00691 0.00117 -0.0543 0.7269 0.1635
-1.250 0.0971 0.00654 0.00104 -0.0542 0.7064 0.2642
-1.000 0.1226 0.00605 0.00091 -0.0540 0.6754 0.4083
-0.750 0.1484 0.00582 0.00088 -0.0536 0.6384 0.5159
-0.500 0.1749 0.00587 0.00092 -0.0533 0.5991 0.5624
-0.250 0.2013 0.00605 0.00098 -0.0528 0.5478 0.5882
0.000 0.2274 0.00632 0.00105 -0.0524 0.4864 0.6044
0.250 0.2538 0.00659 0.00113 -0.0520 0.4315 0.6114
0.500 0.2798 0.00696 0.00122 -0.0517 0.3614 0.6156
0.750 0.3056 0.00737 0.00134 -0.0513 0.2878 0.6193
1.000 0.3314 0.00776 0.00146 -0.0509 0.2195 0.6230
1.250 0.3574 0.00812 0.00160 -0.0506 0.1619 0.6270
1.500 0.3845 0.00835 0.00171 -0.0503 0.1323 0.6312
1.750 0.4118 0.00854 0.00181 -0.0502 0.1138 0.6351
2.250 0.4670 0.00882 0.00201 -0.0498 0.0981 0.6425
2.500 0.4945 0.00895 0.00212 -0.0496 0.0929 0.6463
2.750 0.5222 0.00908 0.00224 -0.0495 0.0890 0.6502
3.000 0.5498 0.00921 0.00235 -0.0493 0.0855 0.6537
3.500 0.6046 0.00950 0.00261 -0.0489 0.0769 0.6604
3.750 0.6319 0.00965 0.00274 -0.0487 0.0721 0.6642
4.000 0.6591 0.00981 0.00289 -0.0485 0.0686 0.6679
4.250 0.6864 0.00996 0.00303 -0.0483 0.0653 0.6714
4.750 0.7405 0.01029 0.00335 -0.0479 0.0584 0.6787
5.000 0.7672 0.01049 0.00352 -0.0476 0.0544 0.6828
5.250 0.7941 0.01067 0.00371 -0.0473 0.0514 0.6868
5.500 0.8206 0.01089 0.00391 -0.0471 0.0482 0.6906
5.750 0.8472 0.01108 0.00411 -0.0468 0.0456 0.6946
6.000 0.8734 0.01130 0.00434 -0.0464 0.0427 0.6994
6.250 0.8998 0.01152 0.00457 -0.0461 0.0403 0.7044
6.500 0.9258 0.01178 0.00482 -0.0458 0.0375 0.7091
6.750 0.9518 0.01200 0.00507 -0.0454 0.0351 0.7140
7.000 0.9774 0.01228 0.00536 -0.0450 0.0324 0.7197
7.250 1.0031 0.01255 0.00564 -0.0446 0.0302 0.7256
7.500 1.0284 0.01285 0.00595 -0.0442 0.0283 0.7324
7.750 1.0537 0.01313 0.00627 -0.0437 0.0270 0.7409
8.000 1.0786 0.01344 0.00661 -0.0432 0.0258 0.7497
8.250 1.1033 0.01377 0.00699 -0.0427 0.0248 0.7601
8.500 1.1280 0.01406 0.00735 -0.0422 0.0242 0.7720
8.750 1.1524 0.01437 0.00772 -0.0416 0.0235 0.7868
9.000 1.1763 0.01468 0.00812 -0.0410 0.0229 0.8079
9.250 1.1987 0.01496 0.00854 -0.0400 0.0224 0.8500
9.500 1.2224 0.01517 0.00899 -0.0393 0.0218 1.0000
9.750 1.2460 0.01560 0.00945 -0.0387 0.0214 1.0000
10.000 1.2697 0.01600 0.00989 -0.0381 0.0210 1.0000
10.250 1.2929 0.01643 0.01036 -0.0374 0.0207 1.0000
10.500 1.3158 0.01688 0.01085 -0.0367 0.0203 1.0000
10.750 1.3382 0.01735 0.01136 -0.0360 0.0200 1.0000
11.000 1.3602 0.01786 0.01190 -0.0352 0.0198 1.0000
11.250 1.3817 0.01838 0.01247 -0.0343 0.0195 1.0000
11.500 1.4026 0.01894 0.01306 -0.0334 0.0192 1.0000
11.750 1.4227 0.01955 0.01371 -0.0324 0.0190 1.0000
12.000 1.4415 0.02023 0.01444 -0.0312 0.0187 1.0000
12.250 1.4593 0.02096 0.01524 -0.0300 0.0185 1.0000
12.500 1.4779 0.02157 0.01590 -0.0288 0.0184 1.0000
12.750 1.4955 0.02221 0.01662 -0.0275 0.0182 1.0000
13.000 1.5120 0.02288 0.01735 -0.0260 0.0181 1.0000
13.250 1.5256 0.02357 0.01812 -0.0241 0.0180 1.0000
13.500 1.5370 0.02430 0.01892 -0.0219 0.0178 1.0000
13.750 1.5473 0.02510 0.01980 -0.0196 0.0177 1.0000
14.000 1.5569 0.02597 0.02075 -0.0174 0.0176 1.0000
14.250 1.5653 0.02694 0.02180 -0.0153 0.0175 1.0000
14.500 1.5734 0.02797 0.02291 -0.0133 0.0173 1.0000
14.750 1.5804 0.02914 0.02416 -0.0115 0.0172 1.0000
15.000 1.5860 0.03045 0.02557 -0.0097 0.0171 1.0000
15.250 1.5911 0.03189 0.02709 -0.0081 0.0170 1.0000
15.500 1.5953 0.03347 0.02877 -0.0068 0.0169 1.0000
15.750 1.5978 0.03529 0.03069 -0.0056 0.0168 1.0000
16.000 1.5993 0.03732 0.03281 -0.0047 0.0167 1.0000
16.250 1.5995 0.03960 0.03520 -0.0040 0.0166 1.0000
16.500 1.5976 0.04225 0.03795 -0.0037 0.0166 1.0000
16.750 1.5945 0.04519 0.04100 -0.0038 0.0165 1.0000
17.000 1.5895 0.04855 0.04448 -0.0042 0.0164 1.0000
17.250 1.5818 0.05248 0.04853 -0.0053 0.0163 1.0000
17.500 1.5705 0.05718 0.05337 -0.0070 0.0163 1.0000
17.750 1.5585 0.06237 0.05867 -0.0093 0.0162 1.0000
18.000 1.5388 0.06920 0.06567 -0.0129 0.0162 1.0000
18.250 1.5179 0.07688 0.07351 -0.0174 0.0161 1.0000
18.500 1.4854 0.08728 0.08412 -0.0238 0.0162 1.0000
18.750 1.4423 0.10054 0.09761 -0.0322 0.0163 1.0000
19.000 1.3870 0.11689 0.11420 -0.0425 0.0163 1.0000
19.250 1.3308 0.13387 0.13139 -0.0534 0.0164 1.0000
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