AH 79-100 B AIRFOIL (ah79100b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-100 B AIRFOIL (ah79100b-il) Reynolds number: 1,000,000 Max Cl/Cd: 183.31 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79100b-il-1000000.txt Download as CSV file: xf-ah79100b-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-100 B 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1015 0.10090 0.09919 -0.0858 0.9785 0.0107
-9.500 -0.0920 0.09787 0.09616 -0.0874 0.9714 0.0117
-9.000 -0.0686 0.08998 0.08827 -0.0953 0.9567 0.0125
-8.750 -0.0510 0.08599 0.08426 -0.0999 0.9499 0.0126
-8.500 -0.0275 0.08141 0.07964 -0.1064 0.9440 0.0126
-8.250 -0.0041 0.07569 0.07390 -0.1141 0.9376 0.0129
-8.000 0.0291 0.07200 0.07016 -0.1213 0.9305 0.0131
-7.750 0.0673 0.06818 0.06628 -0.1303 0.9222 0.0135
-7.500 0.1025 0.06380 0.06180 -0.1397 0.9068 0.0138
-7.250 0.1233 0.06029 0.05817 -0.1452 0.8852 0.0140
-7.000 0.1305 0.05779 0.05557 -0.1467 0.8647 0.0145
-6.750 0.1288 0.05090 0.04860 -0.1531 0.8454 0.0121
-6.500 0.1602 0.01157 0.00706 -0.2044 0.8248 0.0133
-6.250 0.1878 0.01163 0.00712 -0.2044 0.8179 0.0140
-6.000 0.2157 0.01161 0.00703 -0.2045 0.8117 0.0152
-5.750 0.2441 0.01153 0.00686 -0.2047 0.8060 0.0163
-5.500 0.2732 0.01093 0.00615 -0.2055 0.8003 0.0178
-5.250 0.3011 0.01107 0.00625 -0.2055 0.7950 0.0189
-5.000 0.3295 0.01093 0.00606 -0.2058 0.7897 0.0203
-4.750 0.3578 0.01084 0.00587 -0.2059 0.7841 0.0211
-4.500 0.3883 0.00979 0.00465 -0.2070 0.7792 0.0226
-4.250 0.4168 0.00967 0.00452 -0.2072 0.7742 0.0239
-4.000 0.4450 0.00961 0.00442 -0.2074 0.7691 0.0253
-3.750 0.4739 0.00931 0.00403 -0.2077 0.7639 0.0262
-3.500 0.5031 0.00895 0.00362 -0.2081 0.7583 0.0268
-3.250 0.5320 0.00873 0.00332 -0.2084 0.7530 0.0273
-3.000 0.5628 0.00823 0.00273 -0.2092 0.7484 0.0287
-2.750 0.5929 0.00793 0.00240 -0.2099 0.7440 0.0301
-2.500 0.6222 0.00779 0.00221 -0.2102 0.7395 0.0314
-2.250 0.6512 0.00769 0.00206 -0.2105 0.7350 0.0329
-2.000 0.6804 0.00757 0.00192 -0.2109 0.7303 0.0347
-1.750 0.7098 0.00742 0.00172 -0.2112 0.7251 0.0391
-1.500 0.7384 0.00738 0.00165 -0.2114 0.7202 0.0459
-1.250 0.7680 0.00721 0.00156 -0.2119 0.7148 0.0732
-1.000 0.7977 0.00701 0.00153 -0.2125 0.7093 0.1484
-0.750 0.8285 0.00670 0.00155 -0.2136 0.7044 0.3032
-0.500 0.8585 0.00649 0.00161 -0.2143 0.6996 0.4192
-0.250 0.8871 0.00644 0.00167 -0.2145 0.6946 0.4850
0.000 0.9153 0.00646 0.00173 -0.2146 0.6896 0.5286
0.250 0.9436 0.00646 0.00177 -0.2148 0.6844 0.5523
0.500 0.9714 0.00649 0.00182 -0.2148 0.6790 0.5798
0.750 0.9992 0.00651 0.00189 -0.2148 0.6732 0.6079
1.000 1.0271 0.00652 0.00195 -0.2148 0.6666 0.6364
1.250 1.0543 0.00659 0.00202 -0.2148 0.6603 0.6578
1.500 1.0821 0.00660 0.00209 -0.2148 0.6535 0.6772
2.000 1.1366 0.00669 0.00224 -0.2146 0.6382 0.7287
2.250 1.1630 0.00676 0.00234 -0.2143 0.6278 0.7604
2.500 1.1888 0.00682 0.00245 -0.2139 0.6155 0.8036
2.750 1.2134 0.00680 0.00256 -0.2132 0.6042 0.8677
3.000 1.2337 0.00673 0.00259 -0.2115 0.5943 1.0000
3.250 1.2601 0.00688 0.00269 -0.2113 0.5843 1.0000
3.500 1.2864 0.00704 0.00282 -0.2111 0.5739 1.0000
3.750 1.3128 0.00719 0.00295 -0.2109 0.5630 1.0000
4.000 1.3384 0.00738 0.00309 -0.2105 0.5494 1.0000
4.250 1.3626 0.00765 0.00327 -0.2099 0.5287 1.0000
4.500 1.3869 0.00792 0.00346 -0.2093 0.5101 1.0000
4.750 1.4115 0.00817 0.00366 -0.2088 0.4942 1.0000
5.000 1.4354 0.00846 0.00388 -0.2081 0.4738 1.0000
5.250 1.4572 0.00890 0.00418 -0.2071 0.4445 1.0000
5.500 1.4794 0.00930 0.00447 -0.2061 0.4208 1.0000
5.750 1.5015 0.00970 0.00477 -0.2052 0.3964 1.0000
6.000 1.5229 0.01015 0.00511 -0.2041 0.3718 1.0000
6.250 1.5419 0.01076 0.00554 -0.2026 0.3358 1.0000
6.500 1.5587 0.01150 0.00605 -0.2008 0.2938 1.0000
6.750 1.5725 0.01243 0.00669 -0.1984 0.2456 1.0000
7.000 1.5856 0.01336 0.00737 -0.1960 0.2015 1.0000
7.250 1.5958 0.01439 0.00813 -0.1930 0.1567 1.0000
7.500 1.6029 0.01543 0.00895 -0.1894 0.1167 1.0000
7.750 1.6086 0.01654 0.00984 -0.1856 0.0804 1.0000
8.250 1.6304 0.01822 0.01137 -0.1800 0.0503 1.0000
8.500 1.6448 0.01887 0.01203 -0.1779 0.0438 1.0000
8.750 1.6572 0.01966 0.01280 -0.1755 0.0366 1.0000
9.000 1.6658 0.02072 0.01378 -0.1726 0.0236 1.0000
9.250 1.6736 0.02187 0.01490 -0.1697 0.0157 1.0000
9.500 1.6818 0.02304 0.01608 -0.1669 0.0124 1.0000
9.750 1.6937 0.02398 0.01709 -0.1648 0.0113 1.0000
10.000 1.7040 0.02507 0.01821 -0.1626 0.0103 1.0000
10.250 1.7116 0.02640 0.01960 -0.1601 0.0093 1.0000
10.500 1.7197 0.02775 0.02104 -0.1578 0.0088 1.0000
10.750 1.7294 0.02901 0.02237 -0.1558 0.0085 1.0000
11.000 1.7376 0.03043 0.02387 -0.1538 0.0081 1.0000
11.250 1.7454 0.03195 0.02545 -0.1519 0.0078 1.0000
11.500 1.7520 0.03362 0.02720 -0.1499 0.0075 1.0000
11.750 1.7572 0.03548 0.02913 -0.1480 0.0072 1.0000
12.000 1.7593 0.03771 0.03145 -0.1459 0.0069 1.0000
12.250 1.7568 0.04051 0.03439 -0.1436 0.0066 1.0000
12.500 1.7534 0.04354 0.03754 -0.1416 0.0064 1.0000
12.750 1.7573 0.04585 0.03995 -0.1402 0.0063 1.0000
13.000 1.7622 0.04811 0.04230 -0.1389 0.0062 1.0000
13.250 1.7642 0.05079 0.04508 -0.1377 0.0060 1.0000
13.500 1.7674 0.05338 0.04776 -0.1367 0.0059 1.0000
13.750 1.7687 0.05627 0.05075 -0.1357 0.0057 1.0000
14.000 1.7706 0.05919 0.05375 -0.1349 0.0055 1.0000
14.250 1.7697 0.06256 0.05723 -0.1341 0.0054 1.0000
14.500 1.7702 0.06580 0.06057 -0.1336 0.0052 1.0000
14.750 1.7693 0.06932 0.06420 -0.1332 0.0051 1.0000
15.000 1.7668 0.07318 0.06816 -0.1329 0.0050 1.0000
15.250 1.7635 0.07727 0.07235 -0.1328 0.0049 1.0000
15.500 1.7580 0.08178 0.07696 -0.1329 0.0048 1.0000
15.750 1.7495 0.08688 0.08219 -0.1332 0.0047 1.0000
16.000 1.7404 0.09215 0.08759 -0.1337 0.0046 1.0000
16.250 1.7279 0.09810 0.09368 -0.1344 0.0045 1.0000
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