USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 27 AIRFOIL (usa27-il) Reynolds number: 200,000 Max Cl/Cd: 69.42 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa27-il-200000.txt Download as CSV file: xf-usa27-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA 27 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3431 0.11122 0.10792 -0.0332 1.0000 0.0406
-9.000 -0.3578 0.10962 0.10640 -0.0324 1.0000 0.0407
-8.750 -0.3744 0.10806 0.10491 -0.0311 1.0000 0.0407
-8.500 -0.3579 0.10295 0.09980 -0.0276 1.0000 0.0416
-8.250 -0.3579 0.10085 0.09773 -0.0251 1.0000 0.0421
-8.000 -0.3637 0.09906 0.09598 -0.0229 1.0000 0.0427
-7.750 -0.3737 0.09743 0.09440 -0.0207 1.0000 0.0432
-7.500 -0.3669 0.09430 0.09128 -0.0233 0.9970 0.0443
-7.250 -0.3534 0.09022 0.08720 -0.0292 0.9916 0.0463
-7.000 -0.3239 0.08241 0.07916 -0.0528 0.9784 0.0498
-6.750 -0.3140 0.07791 0.07476 -0.0499 0.9760 0.0509
-6.500 -0.2906 0.07489 0.07174 -0.0514 0.9729 0.0523
-6.250 -0.2706 0.07159 0.06841 -0.0544 0.9664 0.0545
-6.000 -0.2295 0.06351 0.05987 -0.0705 0.9585 0.0610
-5.750 -0.2163 0.06043 0.05690 -0.0692 0.9512 0.0621
-5.500 -0.1849 0.05784 0.05431 -0.0715 0.9466 0.0646
-5.250 -0.1521 0.05200 0.04796 -0.0788 0.9363 0.0741
-5.000 -0.1203 0.04902 0.04511 -0.0810 0.9322 0.0762
-4.750 -0.0819 0.04636 0.04239 -0.0847 0.9295 0.0809
-4.500 -0.0614 0.04233 0.03803 -0.0860 0.9189 0.0898
-4.250 -0.0240 0.04030 0.03601 -0.0888 0.9161 0.0952
-4.000 -0.0006 0.03757 0.03307 -0.0894 0.9072 0.1057
-3.750 0.0353 0.03536 0.03071 -0.0920 0.9030 0.1198
-3.500 0.0736 0.03329 0.02851 -0.0947 0.9002 0.1347
-3.250 0.0961 0.03181 0.02691 -0.0940 0.8899 0.1489
-3.000 0.1321 0.03001 0.02502 -0.0958 0.8856 0.1648
-2.750 0.1611 0.02337 0.01701 -0.0937 0.8756 0.1003
-2.500 0.1953 0.02330 0.01739 -0.0963 0.8698 0.1370
-2.250 0.2197 0.02341 0.01769 -0.0958 0.8577 0.1675
-2.000 0.2663 0.01718 0.00957 -0.0944 0.8515 0.0644
-1.750 0.2982 0.01637 0.00857 -0.0944 0.8400 0.0624
-1.500 0.3278 0.01572 0.00782 -0.0942 0.8264 0.0617
-1.250 0.3573 0.01503 0.00707 -0.0940 0.8120 0.0615
-1.000 0.3858 0.01437 0.00638 -0.0937 0.7965 0.0618
-0.750 0.4128 0.01379 0.00579 -0.0932 0.7802 0.0632
-0.500 0.4392 0.01340 0.00537 -0.0926 0.7632 0.0661
-0.250 0.4654 0.01312 0.00501 -0.0919 0.7458 0.0679
0.000 0.4904 0.01294 0.00472 -0.0910 0.7269 0.0698
0.250 0.5156 0.01282 0.00446 -0.0901 0.7077 0.0726
0.500 0.5405 0.01269 0.00422 -0.0892 0.6888 0.0799
0.750 0.5621 0.01227 0.00418 -0.0879 0.6710 0.2186
1.000 0.5839 0.01210 0.00425 -0.0866 0.6538 0.3463
1.250 0.7089 0.01115 0.00456 -0.1069 0.6261 1.0000
1.500 0.7309 0.01140 0.00461 -0.1056 0.6083 1.0000
1.750 0.7523 0.01165 0.00468 -0.1042 0.5905 1.0000
2.000 0.7732 0.01188 0.00475 -0.1028 0.5730 1.0000
2.250 0.7935 0.01209 0.00484 -0.1012 0.5558 1.0000
2.500 0.8140 0.01230 0.00493 -0.0997 0.5400 1.0000
2.750 0.8346 0.01252 0.00502 -0.0982 0.5255 1.0000
3.000 0.8550 0.01273 0.00514 -0.0968 0.5116 1.0000
3.250 0.8758 0.01295 0.00529 -0.0953 0.4989 1.0000
3.500 0.8968 0.01319 0.00545 -0.0940 0.4878 1.0000
3.750 0.9182 0.01347 0.00560 -0.0928 0.4782 1.0000
4.000 0.9393 0.01371 0.00581 -0.0915 0.4682 1.0000
4.250 0.9610 0.01399 0.00602 -0.0903 0.4596 1.0000
4.500 0.9823 0.01427 0.00623 -0.0891 0.4508 1.0000
4.750 1.0037 0.01455 0.00648 -0.0879 0.4425 1.0000
5.000 1.0253 0.01484 0.00672 -0.0867 0.4346 1.0000
5.250 1.0469 0.01513 0.00701 -0.0856 0.4273 1.0000
5.500 1.0688 0.01542 0.00729 -0.0845 0.4206 1.0000
5.750 1.0916 0.01577 0.00760 -0.0837 0.4146 1.0000
6.000 1.1125 0.01604 0.00793 -0.0824 0.4080 1.0000
6.250 1.1356 0.01640 0.00823 -0.0817 0.4021 1.0000
6.500 1.1560 0.01669 0.00860 -0.0803 0.3957 1.0000
6.750 1.1760 0.01697 0.00888 -0.0789 0.3879 1.0000
7.000 1.1935 0.01721 0.00918 -0.0770 0.3785 1.0000
7.250 1.2120 0.01751 0.00941 -0.0754 0.3691 1.0000
7.500 1.2274 0.01768 0.00969 -0.0731 0.3592 1.0000
7.750 1.2433 0.01793 0.00998 -0.0709 0.3489 1.0000
8.000 1.2595 0.01822 0.01022 -0.0689 0.3388 1.0000
8.250 1.2745 0.01843 0.01057 -0.0666 0.3286 1.0000
8.500 1.2899 0.01873 0.01090 -0.0645 0.3186 1.0000
8.750 1.3020 0.01903 0.01121 -0.0618 0.3066 1.0000
9.000 1.3116 0.01933 0.01155 -0.0586 0.2922 1.0000
9.250 1.3224 0.01969 0.01195 -0.0558 0.2763 1.0000
9.500 1.3339 0.02013 0.01242 -0.0532 0.2581 1.0000
9.750 1.3423 0.02077 0.01298 -0.0503 0.2347 1.0000
10.000 1.3485 0.02164 0.01372 -0.0473 0.2071 1.0000
10.250 1.3523 0.02278 0.01472 -0.0442 0.1832 1.0000
10.750 1.3608 0.02532 0.01707 -0.0386 0.1455 1.0000
11.000 1.3672 0.02656 0.01826 -0.0363 0.1241 1.0000
11.250 1.3583 0.02891 0.02026 -0.0327 0.0783 1.0000
11.500 1.3395 0.03216 0.02323 -0.0288 0.0391 1.0000
11.750 1.3374 0.03436 0.02545 -0.0265 0.0347 1.0000
12.000 1.3370 0.03652 0.02772 -0.0247 0.0320 1.0000
12.250 1.3386 0.03864 0.02998 -0.0232 0.0306 1.0000
12.500 1.3383 0.04100 0.03251 -0.0219 0.0294 1.0000
12.750 1.3361 0.04369 0.03536 -0.0208 0.0284 1.0000
13.000 1.3317 0.04676 0.03860 -0.0200 0.0276 1.0000
13.250 1.3255 0.05021 0.04221 -0.0196 0.0271 1.0000
13.500 1.3175 0.05408 0.04624 -0.0195 0.0267 1.0000
13.750 1.3077 0.05833 0.05065 -0.0197 0.0263 1.0000
14.000 1.2964 0.06292 0.05539 -0.0202 0.0261 1.0000
14.250 1.2844 0.06774 0.06036 -0.0209 0.0259 1.0000
14.500 1.2721 0.07272 0.06548 -0.0218 0.0257 1.0000
14.750 1.2600 0.07772 0.07060 -0.0227 0.0256 1.0000
15.000 1.2520 0.08222 0.07521 -0.0236 0.0254 1.0000
15.250 1.2455 0.08651 0.07959 -0.0244 0.0253 1.0000
15.500 1.2408 0.09049 0.08366 -0.0251 0.0252 1.0000
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