AH 80-136 (ah80136-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 80-136 (ah80136-il) Reynolds number: 500,000 Max Cl/Cd: 110.42 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah80136-il-500000.txt Download as CSV file: xf-ah80136-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 80-136
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5580 0.08557 0.08258 0.0170 0.6271 0.0191
-8.000 -0.5668 0.07828 0.07530 0.0083 0.6259 0.0191
-7.750 -0.5700 0.07301 0.06997 0.0045 0.6245 0.0194
-7.500 -0.5683 0.06809 0.06496 0.0017 0.6229 0.0197
-7.250 -0.5638 0.06334 0.06010 -0.0004 0.6214 0.0202
-7.000 -0.5569 0.05857 0.05517 -0.0019 0.6199 0.0207
-6.750 -0.5473 0.05377 0.05016 -0.0027 0.6185 0.0215
-5.500 -0.4772 0.02615 0.02017 0.0019 0.6120 0.0170
-5.250 -0.4536 0.02333 0.01696 0.0027 0.6102 0.0171
-5.000 -0.4280 0.02135 0.01467 0.0033 0.6083 0.0173
-4.750 -0.4010 0.02025 0.01331 0.0036 0.6065 0.0179
-4.500 -0.3759 0.01808 0.01098 0.0039 0.6048 0.0191
-4.250 -0.3485 0.01739 0.01021 0.0040 0.6031 0.0201
-4.000 -0.3211 0.01657 0.00929 0.0042 0.6016 0.0212
-3.750 -0.2936 0.01588 0.00849 0.0044 0.5999 0.0226
-3.500 -0.2652 0.01558 0.00808 0.0044 0.5982 0.0238
-3.250 -0.2395 0.01428 0.00678 0.0047 0.5965 0.0264
-3.000 -0.2110 0.01404 0.00654 0.0045 0.5947 0.0294
-2.750 -0.1822 0.01385 0.00632 0.0044 0.5928 0.0318
-2.500 -0.1558 0.01301 0.00544 0.0046 0.5910 0.0357
-2.250 -0.1275 0.01273 0.00514 0.0045 0.5892 0.0399
-2.000 -0.0990 0.01252 0.00486 0.0044 0.5875 0.0427
-1.750 -0.0714 0.01206 0.00436 0.0044 0.5860 0.0502
-1.500 -0.0430 0.01189 0.00412 0.0043 0.5844 0.0585
-1.250 -0.0159 0.01121 0.00387 0.0042 0.5828 0.1599
-1.000 0.0055 0.00956 0.00366 0.0044 0.5809 0.5463
-0.750 0.0298 0.00893 0.00359 0.0050 0.5789 0.6905
-0.500 0.0513 0.00845 0.00366 0.0068 0.5770 0.8445
-0.250 0.0758 0.00840 0.00378 0.0083 0.5752 0.9206
0.000 0.1064 0.00847 0.00381 0.0082 0.5735 0.9517
0.250 0.1469 0.00863 0.00388 0.0060 0.5718 0.9757
0.500 0.2118 0.00890 0.00403 -0.0014 0.5699 0.9891
0.750 0.2556 0.00898 0.00407 -0.0049 0.5679 0.9947
1.000 0.2957 0.00898 0.00406 -0.0077 0.5656 0.9974
1.250 0.3336 0.00899 0.00403 -0.0100 0.5632 1.0000
1.500 0.3602 0.00897 0.00397 -0.0100 0.5610 1.0000
1.750 0.3866 0.00894 0.00389 -0.0099 0.5588 1.0000
2.000 0.4129 0.00894 0.00381 -0.0097 0.5566 1.0000
2.250 0.4396 0.00898 0.00383 -0.0097 0.5541 1.0000
2.500 0.4668 0.00898 0.00386 -0.0098 0.5513 1.0000
2.750 0.4936 0.00900 0.00388 -0.0098 0.5486 1.0000
3.000 0.5203 0.00900 0.00387 -0.0097 0.5462 1.0000
3.250 0.5468 0.00901 0.00385 -0.0096 0.5440 1.0000
3.500 0.5733 0.00906 0.00385 -0.0094 0.5419 1.0000
3.750 0.6003 0.00913 0.00395 -0.0095 0.5394 1.0000
4.000 0.6275 0.00917 0.00404 -0.0096 0.5364 1.0000
4.250 0.6545 0.00920 0.00409 -0.0096 0.5335 1.0000
4.500 0.6814 0.00922 0.00410 -0.0095 0.5308 1.0000
4.750 0.7082 0.00924 0.00411 -0.0094 0.5283 1.0000
5.000 0.7353 0.00933 0.00421 -0.0095 0.5256 1.0000
5.250 0.7629 0.00938 0.00433 -0.0097 0.5219 1.0000
5.500 0.7903 0.00940 0.00439 -0.0098 0.5183 1.0000
5.750 0.8175 0.00940 0.00441 -0.0097 0.5151 1.0000
6.000 0.8448 0.00945 0.00446 -0.0098 0.5114 1.0000
6.250 0.8727 0.00947 0.00458 -0.0101 0.5063 1.0000
6.500 0.9004 0.00947 0.00461 -0.0102 0.5017 1.0000
6.750 0.9280 0.00951 0.00467 -0.0103 0.4972 1.0000
7.000 0.9562 0.00950 0.00476 -0.0106 0.4897 1.0000
7.250 0.9842 0.00950 0.00478 -0.0109 0.4820 1.0000
7.500 1.0123 0.00951 0.00485 -0.0112 0.4718 1.0000
7.750 1.0406 0.00958 0.00499 -0.0116 0.4602 1.0000
8.000 1.0687 0.00971 0.00514 -0.0120 0.4459 1.0000
8.250 1.0965 0.00993 0.00535 -0.0125 0.4267 1.0000
8.500 1.1237 0.01036 0.00572 -0.0132 0.3948 1.0000
8.750 1.1498 0.01113 0.00633 -0.0141 0.3561 1.0000
9.000 1.1745 0.01212 0.00716 -0.0152 0.3165 1.0000
9.250 1.1973 0.01339 0.00825 -0.0164 0.2737 1.0000
9.500 1.2159 0.01530 0.00989 -0.0181 0.2167 1.0000
9.750 1.2269 0.01882 0.01305 -0.0222 0.1495 1.0000
10.000 1.2238 0.02255 0.01649 -0.0241 0.1010 1.0000
10.250 1.2173 0.02555 0.01931 -0.0236 0.0724 1.0000
10.500 1.2170 0.02800 0.02167 -0.0232 0.0560 1.0000
10.750 1.2190 0.03023 0.02386 -0.0228 0.0447 1.0000
11.000 1.2207 0.03247 0.02608 -0.0223 0.0355 1.0000
11.250 1.2211 0.03485 0.02842 -0.0218 0.0275 1.0000
11.500 1.2220 0.03718 0.03074 -0.0213 0.0221 1.0000
11.750 1.2241 0.03943 0.03306 -0.0208 0.0188 1.0000
12.000 1.2250 0.04183 0.03547 -0.0204 0.0166 1.0000
12.250 1.2226 0.04470 0.03843 -0.0200 0.0149 1.0000
12.500 1.2273 0.04691 0.04072 -0.0198 0.0138 1.0000
12.750 1.2302 0.04935 0.04323 -0.0197 0.0129 1.0000
13.000 1.2317 0.05198 0.04591 -0.0196 0.0121 1.0000
13.250 1.2284 0.05519 0.04919 -0.0195 0.0114 1.0000
13.500 1.2203 0.05898 0.05307 -0.0194 0.0108 1.0000
13.750 1.2247 0.06141 0.05559 -0.0195 0.0105 1.0000
14.000 1.2277 0.06405 0.05831 -0.0196 0.0100 1.0000
14.250 1.2301 0.06679 0.06113 -0.0197 0.0096 1.0000
14.500 1.2323 0.06958 0.06399 -0.0199 0.0092 1.0000
14.750 1.2335 0.07250 0.06698 -0.0202 0.0089 1.0000
15.000 1.2342 0.07553 0.07007 -0.0205 0.0086 1.0000
15.250 1.2337 0.07871 0.07334 -0.0208 0.0084 1.0000
15.500 1.2324 0.08193 0.07661 -0.0210 0.0081 1.0000
15.750 1.2301 0.08516 0.07992 -0.0210 0.0079 1.0000
16.000 1.2280 0.08803 0.08287 -0.0203 0.0077 1.0000
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Polar data table (+)
Polar graphs
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