AH 80-136 (ah80136-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 80-136 (ah80136-il) Reynolds number: 1,000,000 Max Cl/Cd: 138.84 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah80136-il-1000000.txt Download as CSV file: xf-ah80136-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.6423 0.03420 0.03028 0.0022 0.5939 0.0096
-7.000 -0.6496 0.02320 0.01821 0.0054 0.5931 0.0090
-6.750 -0.6289 0.02047 0.01506 0.0064 0.5916 0.0092
-6.500 -0.6038 0.01927 0.01365 0.0068 0.5900 0.0094
-6.250 -0.5817 0.01679 0.01080 0.0076 0.5885 0.0098
-6.000 -0.5565 0.01559 0.00944 0.0080 0.5869 0.0103
-5.750 -0.5296 0.01505 0.00881 0.0081 0.5849 0.0106
-5.500 -0.5023 0.01454 0.00824 0.0081 0.5833 0.0110
-5.250 -0.4750 0.01399 0.00763 0.0082 0.5818 0.0114
-5.000 -0.4477 0.01343 0.00699 0.0083 0.5803 0.0119
-4.750 -0.4202 0.01293 0.00643 0.0084 0.5788 0.0124
-4.500 -0.3924 0.01251 0.00594 0.0085 0.5772 0.0129
-4.250 -0.3657 0.01178 0.00513 0.0087 0.5756 0.0140
-4.000 -0.3374 0.01154 0.00489 0.0086 0.5740 0.0153
-3.750 -0.3090 0.01132 0.00464 0.0085 0.5723 0.0166
-3.500 -0.2802 0.01120 0.00446 0.0083 0.5704 0.0177
-3.250 -0.2527 0.01067 0.00389 0.0084 0.5690 0.0200
-3.000 -0.2239 0.01049 0.00372 0.0082 0.5677 0.0219
-2.750 -0.1949 0.01035 0.00358 0.0080 0.5662 0.0235
-2.500 -0.1666 0.00999 0.00319 0.0079 0.5646 0.0267
-2.250 -0.1376 0.00984 0.00304 0.0076 0.5629 0.0297
-2.000 -0.1085 0.00975 0.00293 0.0074 0.5613 0.0319
-1.750 -0.0799 0.00946 0.00261 0.0073 0.5598 0.0370
-1.500 -0.0509 0.00932 0.00245 0.0070 0.5583 0.0413
-1.250 -0.0219 0.00918 0.00230 0.0068 0.5564 0.0497
-1.000 0.0064 0.00884 0.00216 0.0066 0.5546 0.1097
-0.750 0.0324 0.00790 0.00197 0.0063 0.5534 0.3287
-0.500 0.0583 0.00709 0.00187 0.0063 0.5519 0.5403
-0.250 0.0859 0.00672 0.00181 0.0062 0.5502 0.6336
0.000 0.1108 0.00616 0.00179 0.0068 0.5484 0.7866
0.250 0.1358 0.00590 0.00181 0.0077 0.5468 0.8710
0.500 0.1612 0.00584 0.00185 0.0085 0.5451 0.9194
0.750 0.1870 0.00586 0.00188 0.0093 0.5433 0.9500
1.000 0.2166 0.00597 0.00197 0.0092 0.5411 0.9761
1.250 0.2595 0.00605 0.00204 0.0062 0.5392 0.9861
1.500 0.2979 0.00606 0.00203 0.0039 0.5366 0.9885
1.750 0.3344 0.00607 0.00201 0.0020 0.5339 0.9908
2.000 0.3698 0.00609 0.00200 0.0003 0.5316 0.9933
2.250 0.4052 0.00613 0.00200 -0.0014 0.5294 0.9954
2.500 0.4413 0.00620 0.00202 -0.0034 0.5268 0.9967
2.750 0.4774 0.00620 0.00204 -0.0053 0.5249 0.9984
3.000 0.5130 0.00621 0.00206 -0.0071 0.5226 0.9999
3.250 0.5407 0.00621 0.00206 -0.0072 0.5201 1.0000
3.500 0.5680 0.00622 0.00206 -0.0072 0.5178 1.0000
3.750 0.5952 0.00624 0.00207 -0.0073 0.5153 1.0000
4.000 0.6225 0.00632 0.00211 -0.0074 0.5124 1.0000
4.250 0.6498 0.00632 0.00216 -0.0074 0.5102 1.0000
4.500 0.6770 0.00634 0.00220 -0.0074 0.5073 1.0000
4.750 0.7043 0.00636 0.00224 -0.0075 0.5042 1.0000
5.000 0.7316 0.00640 0.00228 -0.0076 0.5011 1.0000
5.250 0.7590 0.00647 0.00235 -0.0076 0.4975 1.0000
5.500 0.7866 0.00649 0.00241 -0.0078 0.4933 1.0000
5.750 0.8141 0.00653 0.00247 -0.0079 0.4887 1.0000
6.000 0.8418 0.00661 0.00255 -0.0081 0.4842 1.0000
6.250 0.8696 0.00665 0.00264 -0.0083 0.4791 1.0000
6.500 0.8974 0.00673 0.00272 -0.0085 0.4715 1.0000
6.750 0.9254 0.00680 0.00283 -0.0087 0.4635 1.0000
7.000 0.9534 0.00691 0.00294 -0.0091 0.4524 1.0000
7.250 0.9816 0.00707 0.00309 -0.0095 0.4402 1.0000
7.500 1.0097 0.00728 0.00328 -0.0099 0.4223 1.0000
7.750 1.0378 0.00762 0.00355 -0.0106 0.3987 1.0000
8.000 1.0655 0.00828 0.00403 -0.0115 0.3559 1.0000
8.250 1.0926 0.00904 0.00461 -0.0125 0.3159 1.0000
8.500 1.1194 0.00975 0.00519 -0.0134 0.2834 1.0000
8.750 1.1448 0.01077 0.00598 -0.0145 0.2373 1.0000
9.000 1.1670 0.01240 0.00725 -0.0161 0.1725 1.0000
9.250 1.1853 0.01452 0.00897 -0.0179 0.1068 1.0000
9.500 1.2037 0.01695 0.01118 -0.0211 0.0630 1.0000
9.750 1.2223 0.01895 0.01312 -0.0237 0.0466 1.0000
10.000 1.2373 0.02068 0.01482 -0.0250 0.0370 1.0000
10.250 1.2471 0.02231 0.01644 -0.0251 0.0302 1.0000
10.500 1.2555 0.02406 0.01816 -0.0250 0.0233 1.0000
10.750 1.2621 0.02594 0.02002 -0.0248 0.0174 1.0000
11.000 1.2689 0.02778 0.02187 -0.0245 0.0137 1.0000
11.250 1.2722 0.02990 0.02400 -0.0241 0.0109 1.0000
11.500 1.2814 0.03150 0.02566 -0.0239 0.0100 1.0000
11.750 1.2876 0.03334 0.02754 -0.0235 0.0089 1.0000
12.000 1.2888 0.03564 0.02988 -0.0230 0.0078 1.0000
12.250 1.2950 0.03749 0.03180 -0.0227 0.0074 1.0000
12.500 1.3010 0.03937 0.03374 -0.0224 0.0070 1.0000
12.750 1.3066 0.04138 0.03580 -0.0221 0.0066 1.0000
13.000 1.3113 0.04353 0.03801 -0.0219 0.0062 1.0000
13.250 1.3145 0.04585 0.04038 -0.0217 0.0059 1.0000
13.500 1.3136 0.04869 0.04329 -0.0216 0.0056 1.0000
13.750 1.3072 0.05216 0.04687 -0.0214 0.0053 1.0000
14.000 1.3116 0.05451 0.04929 -0.0214 0.0052 1.0000
14.250 1.3148 0.05705 0.05191 -0.0215 0.0051 1.0000
14.500 1.3179 0.05960 0.05453 -0.0215 0.0050 1.0000
14.750 1.3191 0.06242 0.05743 -0.0217 0.0049 1.0000
15.000 1.3205 0.06526 0.06034 -0.0219 0.0048 1.0000
15.250 1.3206 0.06831 0.06347 -0.0221 0.0047 1.0000
15.500 1.3208 0.07136 0.06660 -0.0224 0.0046 1.0000
15.750 1.3206 0.07451 0.06982 -0.0228 0.0045 1.0000
16.000 1.3194 0.07785 0.07325 -0.0233 0.0044 1.0000
16.250 1.3190 0.08112 0.07659 -0.0238 0.0043 1.0000
16.500 1.3171 0.08460 0.08014 -0.0244 0.0042 1.0000
16.750 1.3151 0.08817 0.08379 -0.0251 0.0041 1.0000
17.000 1.3131 0.09178 0.08748 -0.0258 0.0041 1.0000
17.250 1.3101 0.09559 0.09137 -0.0267 0.0040 1.0000
17.500 1.3064 0.09951 0.09538 -0.0277 0.0039 1.0000
17.750 1.3026 0.10350 0.09945 -0.0287 0.0039 1.0000
18.000 1.2975 0.10773 0.10377 -0.0299 0.0038 1.0000
18.250 1.2918 0.11213 0.10825 -0.0312 0.0037 1.0000
18.500 1.2848 0.11669 0.11291 -0.0325 0.0037 1.0000
18.750 1.2777 0.12129 0.11760 -0.0340 0.0036 1.0000
19.000 1.2704 0.12601 0.12242 -0.0355 0.0036 1.0000
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Polar data table (+)
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