AH 79-100 B AIRFOIL (ah79100b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 79-100 B AIRFOIL (ah79100b-il) Reynolds number: 500,000 Max Cl/Cd: 148.35 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah79100b-il-500000.txt Download as CSV file: xf-ah79100b-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0072 0.08493 0.08270 -0.0925 0.9572 0.0175
-9.500 -0.1259 0.10314 0.10082 -0.0831 0.9756 0.0165
-9.250 -0.1126 0.09851 0.09620 -0.0849 0.9718 0.0167
-9.000 -0.0931 0.09537 0.09305 -0.0865 0.9694 0.0172
-8.750 -0.0743 0.09193 0.08960 -0.0903 0.9671 0.0176
-8.500 -0.0624 0.08889 0.08656 -0.0924 0.9585 0.0181
-8.250 -0.0443 0.08526 0.08293 -0.0966 0.9548 0.0186
-8.000 -0.0296 0.08192 0.07958 -0.0998 0.9463 0.0191
-7.750 -0.0068 0.07773 0.07538 -0.1060 0.9421 0.0201
-7.500 0.0173 0.07306 0.07068 -0.1151 0.9332 0.0210
-7.250 0.0522 0.06759 0.06516 -0.1266 0.9273 0.0212
-7.000 0.0821 0.06250 0.06001 -0.1360 0.9161 0.0213
-6.750 0.1040 0.05711 0.05457 -0.1431 0.9056 0.0218
-6.500 0.1300 0.05375 0.05113 -0.1490 0.8951 0.0221
-6.250 0.1524 0.05192 0.04924 -0.1517 0.8850 0.0236
-6.000 0.1721 0.04821 0.04546 -0.1577 0.8725 0.0246
-5.750 0.2137 0.03869 0.03568 -0.1774 0.8597 0.0274
-5.500 0.2438 0.03266 0.02925 -0.1861 0.8507 0.0275
-5.250 0.2647 0.02843 0.02494 -0.1903 0.8428 0.0292
-5.000 0.2914 0.02724 0.02365 -0.1920 0.8365 0.0316
-4.750 0.3289 0.02304 0.01894 -0.1969 0.8303 0.0345
-4.500 0.3758 0.01512 0.00990 -0.2044 0.8259 0.0299
-4.250 0.4039 0.01479 0.00950 -0.2048 0.8201 0.0323
-4.000 0.4343 0.01399 0.00846 -0.2055 0.8146 0.0342
-3.750 0.4657 0.01318 0.00740 -0.2064 0.8098 0.0349
-3.500 0.4945 0.01253 0.00661 -0.2067 0.8042 0.0354
-3.250 0.5251 0.01131 0.00522 -0.2076 0.7989 0.0367
-3.000 0.5554 0.01068 0.00451 -0.2083 0.7939 0.0383
-2.750 0.5841 0.01028 0.00408 -0.2086 0.7880 0.0396
-2.500 0.6138 0.00998 0.00371 -0.2090 0.7826 0.0414
-2.250 0.6434 0.00974 0.00342 -0.2095 0.7774 0.0435
-2.000 0.6721 0.00958 0.00322 -0.2097 0.7718 0.0459
-1.750 0.7033 0.00926 0.00284 -0.2105 0.7670 0.0531
-1.500 0.7331 0.00908 0.00265 -0.2110 0.7620 0.0657
-1.250 0.7637 0.00874 0.00252 -0.2118 0.7566 0.1423
-1.000 0.7967 0.00818 0.00258 -0.2137 0.7520 0.4025
-0.750 0.8256 0.00810 0.00268 -0.2140 0.7472 0.4970
-0.500 0.8535 0.00809 0.00275 -0.2140 0.7416 0.5472
-0.250 0.8817 0.00813 0.00278 -0.2141 0.7362 0.5812
0.000 0.9090 0.00813 0.00284 -0.2139 0.7302 0.6085
0.250 0.9365 0.00814 0.00289 -0.2138 0.7244 0.6424
0.500 0.9643 0.00818 0.00296 -0.2138 0.7194 0.6749
0.750 0.9912 0.00818 0.00304 -0.2136 0.7135 0.7034
1.000 1.0186 0.00820 0.00308 -0.2134 0.7082 0.7263
1.250 1.0457 0.00823 0.00316 -0.2133 0.7029 0.7545
1.500 1.0719 0.00822 0.00325 -0.2129 0.6966 0.7881
1.750 1.0974 0.00823 0.00330 -0.2123 0.6909 0.8326
2.000 1.1140 0.00798 0.00328 -0.2097 0.6839 1.0000
2.250 1.1420 0.00810 0.00333 -0.2098 0.6772 1.0000
2.500 1.1693 0.00819 0.00342 -0.2097 0.6697 1.0000
2.750 1.1965 0.00831 0.00349 -0.2096 0.6623 1.0000
3.000 1.2231 0.00840 0.00359 -0.2095 0.6538 1.0000
3.250 1.2493 0.00854 0.00367 -0.2091 0.6442 1.0000
3.500 1.2749 0.00867 0.00377 -0.2087 0.6328 1.0000
3.750 1.3005 0.00879 0.00390 -0.2083 0.6209 1.0000
4.000 1.3262 0.00894 0.00403 -0.2079 0.6105 1.0000
4.250 1.3517 0.00912 0.00418 -0.2075 0.6004 1.0000
4.500 1.3767 0.00929 0.00435 -0.2070 0.5885 1.0000
4.750 1.4010 0.00950 0.00454 -0.2063 0.5746 1.0000
5.000 1.4246 0.00974 0.00474 -0.2055 0.5589 1.0000
5.250 1.4479 0.01000 0.00498 -0.2047 0.5428 1.0000
5.500 1.4710 0.01028 0.00522 -0.2039 0.5260 1.0000
5.750 1.4931 0.01061 0.00550 -0.2028 0.5069 1.0000
6.000 1.5138 0.01100 0.00582 -0.2016 0.4849 1.0000
6.250 1.5332 0.01146 0.00620 -0.2000 0.4577 1.0000
6.500 1.5519 0.01197 0.00660 -0.1984 0.4319 1.0000
6.750 1.5694 0.01254 0.00706 -0.1966 0.4031 1.0000
7.000 1.5849 0.01322 0.00758 -0.1945 0.3713 1.0000
7.250 1.5989 0.01396 0.00817 -0.1921 0.3360 1.0000
7.500 1.6086 0.01485 0.00886 -0.1890 0.2958 1.0000
7.750 1.6134 0.01598 0.00972 -0.1850 0.2490 1.0000
8.000 1.6166 0.01726 0.01073 -0.1810 0.2035 1.0000
8.250 1.6189 0.01865 0.01186 -0.1769 0.1587 1.0000
8.500 1.6193 0.02023 0.01318 -0.1727 0.1152 1.0000
8.750 1.6199 0.02185 0.01459 -0.1688 0.0805 1.0000
9.000 1.6252 0.02323 0.01589 -0.1657 0.0630 1.0000
9.250 1.6326 0.02451 0.01716 -0.1630 0.0522 1.0000
9.500 1.6397 0.02587 0.01851 -0.1604 0.0417 1.0000
9.750 1.6430 0.02758 0.02016 -0.1575 0.0278 1.0000
10.000 1.6459 0.02943 0.02199 -0.1546 0.0208 1.0000
10.250 1.6502 0.03122 0.02383 -0.1521 0.0180 1.0000
10.500 1.6520 0.03334 0.02604 -0.1495 0.0162 1.0000
10.750 1.6586 0.03507 0.02788 -0.1475 0.0153 1.0000
11.000 1.6636 0.03701 0.02993 -0.1456 0.0144 1.0000
11.250 1.6679 0.03908 0.03209 -0.1437 0.0136 1.0000
11.500 1.6678 0.04167 0.03477 -0.1417 0.0129 1.0000
11.750 1.6604 0.04516 0.03839 -0.1394 0.0122 1.0000
12.000 1.6654 0.04739 0.04073 -0.1381 0.0119 1.0000
12.250 1.6681 0.04997 0.04342 -0.1368 0.0115 1.0000
12.500 1.6696 0.05275 0.04632 -0.1355 0.0111 1.0000
12.750 1.6697 0.05579 0.04947 -0.1344 0.0108 1.0000
13.000 1.6703 0.05885 0.05264 -0.1334 0.0105 1.0000
13.250 1.6704 0.06207 0.05597 -0.1325 0.0101 1.0000
13.500 1.6692 0.06554 0.05955 -0.1318 0.0099 1.0000
13.750 1.6677 0.06912 0.06323 -0.1312 0.0097 1.0000
14.000 1.6651 0.07295 0.06716 -0.1307 0.0095 1.0000
14.250 1.6591 0.07734 0.07167 -0.1301 0.0092 1.0000
14.500 1.6547 0.08154 0.07599 -0.1295 0.0090 1.0000
14.750 1.6536 0.08532 0.07990 -0.1290 0.0089 1.0000
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Polar data table (+)
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