RAF 34 AIRFOIL (raf34-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 34 AIRFOIL (raf34-il) Reynolds number: 200,000 Max Cl/Cd: 65.24 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf34-il-200000-n5.txt Download as CSV file: xf-raf34-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 34 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7296 0.06306 0.05900 -0.0472 1.0000 0.0275
-12.000 -0.7653 0.05556 0.05128 -0.0520 1.0000 0.0274
-11.750 -0.7947 0.05060 0.04608 -0.0526 1.0000 0.0274
-11.500 -0.8199 0.04687 0.04208 -0.0506 1.0000 0.0276
-11.250 -0.8410 0.04393 0.03884 -0.0468 1.0000 0.0278
-11.000 -0.8562 0.04145 0.03605 -0.0426 1.0000 0.0281
-10.750 -0.8619 0.03908 0.03338 -0.0393 1.0000 0.0286
-10.500 -0.8550 0.03727 0.03150 -0.0373 1.0000 0.0291
-10.250 -0.8451 0.03594 0.03010 -0.0354 1.0000 0.0297
-10.000 -0.8347 0.03467 0.02870 -0.0335 1.0000 0.0303
-9.750 -0.8246 0.03318 0.02705 -0.0314 1.0000 0.0309
-9.500 -0.8132 0.03172 0.02539 -0.0293 1.0000 0.0316
-9.250 -0.8009 0.03030 0.02376 -0.0273 1.0000 0.0323
-9.000 -0.7877 0.02901 0.02226 -0.0252 1.0000 0.0331
-8.750 -0.7740 0.02781 0.02084 -0.0231 1.0000 0.0339
-8.500 -0.7531 0.02659 0.01937 -0.0224 0.9930 0.0346
-8.250 -0.7211 0.02496 0.01751 -0.0240 0.9664 0.0352
-8.000 -0.6852 0.02342 0.01587 -0.0264 0.9427 0.0362
-7.750 -0.6483 0.02237 0.01473 -0.0288 0.9214 0.0374
-7.500 -0.6142 0.02142 0.01364 -0.0303 0.9013 0.0385
-7.250 -0.5845 0.02055 0.01262 -0.0309 0.8823 0.0393
-7.000 -0.5576 0.01979 0.01169 -0.0309 0.8652 0.0401
-6.750 -0.5326 0.01911 0.01088 -0.0303 0.8496 0.0409
-6.500 -0.5087 0.01853 0.01017 -0.0296 0.8353 0.0417
-6.250 -0.4851 0.01805 0.00954 -0.0287 0.8219 0.0426
-6.000 -0.4634 0.01736 0.00882 -0.0277 0.8096 0.0438
-5.750 -0.4412 0.01683 0.00823 -0.0266 0.7984 0.0451
-5.500 -0.4185 0.01640 0.00771 -0.0256 0.7876 0.0462
-5.250 -0.3956 0.01599 0.00723 -0.0246 0.7770 0.0475
-5.000 -0.3724 0.01563 0.00677 -0.0236 0.7673 0.0490
-4.750 -0.3488 0.01530 0.00634 -0.0227 0.7576 0.0508
-4.500 -0.3254 0.01494 0.00594 -0.0218 0.7484 0.0532
-4.250 -0.3018 0.01461 0.00557 -0.0209 0.7398 0.0577
-4.000 -0.2780 0.01428 0.00525 -0.0201 0.7309 0.0657
-3.750 -0.2545 0.01395 0.00497 -0.0192 0.7229 0.0830
-3.500 -0.2305 0.01364 0.00472 -0.0185 0.7143 0.1069
-3.250 -0.2063 0.01340 0.00448 -0.0177 0.7068 0.1283
-3.000 -0.1821 0.01313 0.00427 -0.0170 0.6985 0.1503
-2.750 -0.1585 0.01285 0.00406 -0.0162 0.6913 0.1805
-2.500 -0.1362 0.01245 0.00390 -0.0152 0.6833 0.2396
-2.250 -0.1146 0.01204 0.00372 -0.0141 0.6763 0.3083
-2.000 -0.0955 0.01149 0.00355 -0.0124 0.6689 0.3996
-1.750 -0.0806 0.01083 0.00346 -0.0098 0.6618 0.5417
-1.500 -0.0621 0.01037 0.00345 -0.0076 0.6551 0.6585
-1.250 -0.0363 0.01014 0.00350 -0.0066 0.6476 0.7435
-1.000 -0.0035 0.01009 0.00355 -0.0071 0.6408 0.8003
-0.750 0.0325 0.01012 0.00360 -0.0085 0.6327 0.8349
-0.500 0.0732 0.01024 0.00366 -0.0107 0.6257 0.8627
-0.250 0.1160 0.01040 0.00381 -0.0134 0.6171 0.8887
0.250 0.1978 0.01080 0.00409 -0.0179 0.6015 0.9218
0.500 0.2286 0.01095 0.00414 -0.0183 0.5943 0.9320
0.750 0.2676 0.01108 0.00423 -0.0205 0.5855 0.9378
1.000 0.2992 0.01121 0.00428 -0.0211 0.5782 0.9471
1.250 0.3383 0.01131 0.00436 -0.0234 0.5691 0.9526
1.500 0.3678 0.01142 0.00439 -0.0237 0.5617 0.9603
1.750 0.4041 0.01146 0.00442 -0.0255 0.5522 0.9637
2.000 0.4371 0.01153 0.00444 -0.0266 0.5425 0.9687
2.250 0.4682 0.01160 0.00445 -0.0273 0.5314 0.9739
2.500 0.5031 0.01164 0.00448 -0.0289 0.5199 0.9777
2.750 0.5350 0.01172 0.00453 -0.0299 0.5087 0.9827
3.000 0.5692 0.01178 0.00454 -0.0313 0.4982 0.9864
3.250 0.6033 0.01183 0.00458 -0.0328 0.4867 0.9902
3.500 0.6364 0.01190 0.00465 -0.0341 0.4745 0.9941
3.750 0.6710 0.01195 0.00467 -0.0357 0.4625 0.9976
4.000 0.7017 0.01204 0.00474 -0.0365 0.4511 1.0000
4.250 0.7235 0.01214 0.00485 -0.0355 0.4410 1.0000
4.500 0.7452 0.01226 0.00498 -0.0344 0.4312 1.0000
4.750 0.7665 0.01241 0.00511 -0.0332 0.4199 1.0000
5.000 0.7879 0.01257 0.00526 -0.0321 0.4078 1.0000
5.250 0.8093 0.01273 0.00544 -0.0310 0.3967 1.0000
5.500 0.8303 0.01292 0.00565 -0.0298 0.3848 1.0000
5.750 0.8511 0.01314 0.00586 -0.0285 0.3735 1.0000
6.000 0.8713 0.01339 0.00609 -0.0272 0.3588 1.0000
6.250 0.8912 0.01366 0.00634 -0.0258 0.3422 1.0000
6.500 0.9105 0.01397 0.00663 -0.0244 0.3235 1.0000
6.750 0.9294 0.01430 0.00694 -0.0229 0.3053 1.0000
7.000 0.9470 0.01471 0.00728 -0.0212 0.2843 1.0000
7.250 0.9644 0.01513 0.00766 -0.0195 0.2614 1.0000
7.500 0.9808 0.01562 0.00809 -0.0177 0.2392 1.0000
7.750 0.9965 0.01614 0.00855 -0.0158 0.2163 1.0000
8.000 1.0101 0.01678 0.00909 -0.0137 0.1901 1.0000
8.250 1.0214 0.01755 0.00971 -0.0112 0.1618 1.0000
8.500 1.0324 0.01831 0.01038 -0.0087 0.1420 1.0000
8.750 1.0430 0.01905 0.01107 -0.0062 0.1275 1.0000
9.000 1.0532 0.01978 0.01177 -0.0036 0.1151 1.0000
9.250 1.0627 0.02050 0.01249 -0.0009 0.1027 1.0000
9.500 1.0716 0.02124 0.01321 0.0018 0.0846 1.0000
9.750 1.0717 0.02223 0.01405 0.0057 0.0648 1.0000
10.000 1.0703 0.02320 0.01497 0.0098 0.0569 1.0000
10.250 1.0698 0.02432 0.01608 0.0132 0.0516 1.0000
10.500 1.0723 0.02547 0.01728 0.0158 0.0478 1.0000
10.750 1.0752 0.02676 0.01863 0.0180 0.0447 1.0000
11.000 1.0759 0.02836 0.02027 0.0200 0.0420 1.0000
11.250 1.0792 0.02989 0.02188 0.0215 0.0400 1.0000
11.500 1.0837 0.03145 0.02354 0.0228 0.0378 1.0000
11.750 1.0865 0.03324 0.02541 0.0239 0.0360 1.0000
12.000 1.0864 0.03537 0.02759 0.0249 0.0344 1.0000
12.250 1.0873 0.03751 0.02981 0.0256 0.0332 1.0000
12.500 1.0906 0.03950 0.03192 0.0262 0.0317 1.0000
12.750 1.0923 0.04170 0.03421 0.0267 0.0304 1.0000
13.000 1.0930 0.04407 0.03665 0.0270 0.0292 1.0000
13.250 1.0927 0.04659 0.03924 0.0272 0.0284 1.0000
13.500 1.0886 0.04956 0.04224 0.0272 0.0274 1.0000
13.750 1.0912 0.05191 0.04472 0.0273 0.0263 1.0000
14.000 1.0916 0.05452 0.04744 0.0273 0.0255 1.0000
14.250 1.0917 0.05727 0.05029 0.0271 0.0246 1.0000
14.500 1.0913 0.06015 0.05325 0.0268 0.0239 1.0000
14.750 1.0909 0.06313 0.05630 0.0262 0.0231 1.0000
15.000 1.0901 0.06617 0.05941 0.0257 0.0227 1.0000
15.250 1.0880 0.06941 0.06269 0.0251 0.0222 1.0000
15.500 1.0881 0.07246 0.06585 0.0246 0.0216 1.0000
15.750 1.0880 0.07568 0.06921 0.0238 0.0208 1.0000
16.000 1.0877 0.07894 0.07259 0.0230 0.0203 1.0000
16.250 1.0863 0.08243 0.07618 0.0220 0.0197 1.0000
16.500 1.0847 0.08597 0.07982 0.0209 0.0192 1.0000
16.750 1.0830 0.08959 0.08352 0.0198 0.0188 1.0000
17.000 1.0809 0.09334 0.08737 0.0185 0.0184 1.0000
17.250 1.0785 0.09714 0.09125 0.0171 0.0181 1.0000
17.500 1.0755 0.10101 0.09516 0.0157 0.0177 1.0000
17.750 1.0735 0.10477 0.09901 0.0145 0.0175 1.0000
18.000 1.0670 0.10967 0.10409 0.0123 0.0172 1.0000
18.250 1.0600 0.11467 0.10926 0.0101 0.0168 1.0000
18.500 1.0525 0.11981 0.11455 0.0078 0.0165 1.0000
18.750 1.0444 0.12520 0.12009 0.0052 0.0163 1.0000
19.000 1.0347 0.13109 0.12614 0.0021 0.0161 1.0000
19.250 1.0239 0.13735 0.13254 -0.0012 0.0159 1.0000
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