AH 79-100 C AIRFOIL (ah79100c-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-100 C AIRFOIL (ah79100c-il) Reynolds number: 200,000 Max Cl/Cd: 97.57 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79100c-il-200000.txt Download as CSV file: xf-ah79100c-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-100 C 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1622 0.10821 0.10476 -0.0708 0.9567 0.0354
-8.000 -0.1585 0.10628 0.10284 -0.0776 0.9507 0.0381
-7.750 -0.1563 0.10402 0.10061 -0.0815 0.9436 0.0384
-7.500 -0.1426 0.09890 0.09550 -0.0850 0.9414 0.0389
-7.250 -0.1357 0.09596 0.09256 -0.0824 0.9349 0.0394
-7.000 -0.1177 0.09260 0.08919 -0.0834 0.9319 0.0405
-6.750 -0.1009 0.08940 0.08598 -0.0864 0.9293 0.0419
-6.500 -0.1054 0.08775 0.08436 -0.0848 0.9201 0.0425
-6.250 -0.0887 0.08418 0.08077 -0.0894 0.9165 0.0444
-6.000 -0.0869 0.08164 0.07826 -0.0915 0.9067 0.0461
-5.750 -0.0413 0.07472 0.07124 -0.1142 0.9018 0.0478
-5.500 -0.0493 0.07150 0.06807 -0.1107 0.8926 0.0484
-5.250 -0.0361 0.06893 0.06550 -0.1082 0.8902 0.0496
-5.000 -0.0096 0.06569 0.06223 -0.1114 0.8884 0.0517
-4.750 -0.0017 0.06332 0.05985 -0.1126 0.8799 0.0539
-4.500 0.0617 0.05333 0.04955 -0.1351 0.8763 0.0601
-4.250 0.0818 0.05186 0.04814 -0.1338 0.8745 0.0627
-4.000 0.1375 0.04556 0.04154 -0.1465 0.8735 0.0748
-3.750 0.1454 0.04457 0.04055 -0.1444 0.8651 0.0780
-3.500 0.1899 0.04063 0.03637 -0.1514 0.8629 0.0921
-3.250 0.2818 0.02846 0.02268 -0.1693 0.8651 0.0641
-3.000 0.3286 0.02544 0.01896 -0.1736 0.8639 0.0627
-2.750 0.3705 0.02358 0.01664 -0.1764 0.8626 0.0621
-2.500 0.4103 0.02232 0.01516 -0.1787 0.8613 0.0639
-2.250 0.4501 0.02131 0.01400 -0.1810 0.8602 0.0675
-2.000 0.4907 0.02044 0.01295 -0.1831 0.8592 0.0719
-1.750 0.5325 0.01920 0.01175 -0.1859 0.8586 0.0803
-1.500 0.5757 0.01829 0.01085 -0.1889 0.8579 0.0969
-1.250 0.5860 0.01858 0.01118 -0.1858 0.8483 0.1116
-1.000 0.6269 0.01783 0.01060 -0.1884 0.8468 0.1608
-0.750 0.6705 0.01694 0.01015 -0.1918 0.8457 0.2842
-0.500 0.7147 0.01620 0.00977 -0.1951 0.8446 0.4179
-0.250 0.7559 0.01523 0.00954 -0.1977 0.8436 0.6718
0.500 0.8405 0.01451 0.00895 -0.1968 0.8298 1.0000
0.750 0.8862 0.01416 0.00848 -0.2003 0.8280 1.0000
1.000 0.8980 0.01460 0.00887 -0.1971 0.8187 1.0000
1.250 0.9391 0.01435 0.00853 -0.1997 0.8157 1.0000
1.500 0.9830 0.01408 0.00817 -0.2028 0.8131 1.0000
1.750 0.9980 0.01441 0.00849 -0.2002 0.8041 1.0000
2.000 1.0382 0.01417 0.00818 -0.2025 0.8000 1.0000
2.250 1.0659 0.01425 0.00824 -0.2025 0.7937 1.0000
2.500 1.0943 0.01430 0.00828 -0.2026 0.7872 1.0000
2.750 1.1364 0.01407 0.00798 -0.2053 0.7829 1.0000
3.000 1.1534 0.01431 0.00825 -0.2030 0.7735 1.0000
3.250 1.1930 0.01412 0.00802 -0.2052 0.7680 1.0000
3.500 1.2111 0.01436 0.00830 -0.2032 0.7590 1.0000
3.750 1.2484 0.01424 0.00814 -0.2050 0.7529 1.0000
4.000 1.2667 0.01442 0.00837 -0.2030 0.7430 1.0000
4.250 1.3001 0.01436 0.00830 -0.2039 0.7353 1.0000
4.500 1.3217 0.01447 0.00845 -0.2025 0.7252 1.0000
4.750 1.3447 0.01455 0.00856 -0.2014 0.7147 1.0000
5.000 1.3744 0.01453 0.00854 -0.2016 0.7049 1.0000
5.250 1.3950 0.01465 0.00872 -0.2000 0.6937 1.0000
5.500 1.4154 0.01481 0.00893 -0.1984 0.6826 1.0000
5.750 1.4383 0.01492 0.00907 -0.1973 0.6709 1.0000
6.000 1.4602 0.01502 0.00921 -0.1959 0.6579 1.0000
6.250 1.4791 0.01516 0.00938 -0.1940 0.6432 1.0000
6.500 1.4946 0.01533 0.00959 -0.1913 0.6265 1.0000
6.750 1.5072 0.01553 0.00980 -0.1881 0.6072 1.0000
7.000 1.5196 0.01577 0.01001 -0.1848 0.5861 1.0000
7.250 1.5269 0.01613 0.01034 -0.1806 0.5610 1.0000
7.500 1.5333 0.01661 0.01071 -0.1763 0.5316 1.0000
7.750 1.5376 0.01726 0.01122 -0.1718 0.4987 1.0000
8.000 1.5412 0.01807 0.01186 -0.1674 0.4658 1.0000
8.250 1.5421 0.01907 0.01268 -0.1626 0.4307 1.0000
8.500 1.5432 0.02015 0.01362 -0.1581 0.3964 1.0000
8.750 1.5448 0.02132 0.01466 -0.1539 0.3647 1.0000
9.000 1.5466 0.02258 0.01579 -0.1500 0.3342 1.0000
9.250 1.5479 0.02395 0.01705 -0.1462 0.3041 1.0000
9.500 1.5477 0.02551 0.01848 -0.1423 0.2706 1.0000
9.750 1.5462 0.02728 0.02008 -0.1385 0.2367 1.0000
10.000 1.5424 0.02936 0.02196 -0.1347 0.1956 1.0000
10.250 1.5330 0.03205 0.02430 -0.1306 0.1427 1.0000
10.500 1.5136 0.03587 0.02754 -0.1259 0.0725 1.0000
10.750 1.5021 0.03927 0.03067 -0.1222 0.0429 1.0000
11.000 1.5020 0.04176 0.03322 -0.1197 0.0359 1.0000
11.250 1.4999 0.04451 0.03603 -0.1173 0.0323 1.0000
11.500 1.5034 0.04676 0.03842 -0.1154 0.0303 1.0000
11.750 1.5055 0.04921 0.04099 -0.1137 0.0284 1.0000
12.000 1.5047 0.05205 0.04393 -0.1120 0.0271 1.0000
12.250 1.5002 0.05538 0.04737 -0.1103 0.0262 1.0000
12.500 1.4980 0.05858 0.05068 -0.1087 0.0257 1.0000
12.750 1.4993 0.06146 0.05368 -0.1075 0.0252 1.0000
13.000 1.5012 0.06434 0.05668 -0.1063 0.0247 1.0000
13.250 1.5039 0.06715 0.05961 -0.1052 0.0242 1.0000
13.500 1.5081 0.06986 0.06242 -0.1041 0.0237 1.0000
13.750 1.5144 0.07236 0.06502 -0.1031 0.0233 1.0000
14.000 1.5227 0.07466 0.06743 -0.1021 0.0229 1.0000
14.250 1.5334 0.07675 0.06962 -0.1010 0.0226 1.0000
14.500 1.5460 0.07874 0.07173 -0.0999 0.0224 1.0000
14.750 1.5582 0.08086 0.07398 -0.0990 0.0221 1.0000
15.000 1.5688 0.08320 0.07643 -0.0983 0.0216 1.0000
15.250 1.5829 0.08544 0.07876 -0.0975 0.0210 1.0000
15.500 1.5981 0.08817 0.08169 -0.0967 0.0207 1.0000
15.750 1.6020 0.09164 0.08541 -0.0962 0.0207 1.0000
16.000 1.6012 0.09550 0.08952 -0.0959 0.0207 1.0000
16.250 1.5960 0.09964 0.09392 -0.0959 0.0209 1.0000
16.500 1.5881 0.10418 0.09874 -0.0963 0.0210 1.0000
16.750 1.5764 0.10926 0.10412 -0.0972 0.0211 1.0000
17.000 1.5618 0.11501 0.11019 -0.0986 0.0214 1.0000
17.250 1.5389 0.12232 0.11789 -0.1012 0.0218 1.0000
17.500 1.5106 0.13106 0.12702 -0.1053 0.0224 1.0000
17.750 1.4868 0.13960 0.13587 -0.1098 0.0228 1.0000
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