AH 83-150 Q (ah83150q-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 83-150 Q (ah83150q-il) Reynolds number: 500,000 Max Cl/Cd: 109.73 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah83150q-il-500000.txt Download as CSV file: xf-ah83150q-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 83-150 Q
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1718 0.08479 0.08162 -0.0560 0.7142 0.0162
-9.750 -0.1781 0.07867 0.07551 -0.0596 0.7131 0.0163
-9.500 -0.1816 0.07348 0.07035 -0.0615 0.7116 0.0164
-9.250 -0.1839 0.06850 0.06538 -0.0641 0.7101 0.0164
-9.000 -0.1789 0.06629 0.06317 -0.0636 0.7080 0.0168
-8.750 -0.1810 0.06198 0.05886 -0.0657 0.7063 0.0169
-8.500 -0.1827 0.05819 0.05507 -0.0676 0.7047 0.0173
-8.250 -0.2710 0.05992 0.05644 -0.0798 0.7081 0.0162
-8.000 -0.2914 0.05482 0.05114 -0.0790 0.7060 0.0164
-7.750 -0.2888 0.05201 0.04827 -0.0786 0.7040 0.0166
-7.500 -0.2837 0.04970 0.04589 -0.0781 0.7021 0.0167
-7.250 -0.2746 0.04800 0.04416 -0.0778 0.7003 0.0171
-7.000 -0.2656 0.04545 0.04151 -0.0773 0.6985 0.0174
-6.750 -0.2546 0.04293 0.03886 -0.0768 0.6964 0.0181
-6.500 -0.2440 0.03986 0.03513 -0.0743 0.6943 0.0204
-6.250 -0.2343 0.03535 0.03054 -0.0739 0.6924 0.0210
-6.000 -0.2158 0.03354 0.02867 -0.0738 0.6904 0.0215
-5.750 -0.1959 0.03210 0.02712 -0.0735 0.6886 0.0225
-5.500 -0.1727 0.03258 0.02694 -0.0716 0.6869 0.0255
-5.250 -0.1561 0.02792 0.02234 -0.0719 0.6851 0.0268
-5.000 -0.1327 0.02655 0.02092 -0.0718 0.6832 0.0280
-4.750 -0.1051 0.02753 0.02149 -0.0709 0.6810 0.0317
-4.500 -0.0849 0.02345 0.01736 -0.0709 0.6792 0.0336
-4.250 -0.0593 0.02238 0.01620 -0.0709 0.6772 0.0358
-3.750 -0.0071 0.02010 0.01363 -0.0706 0.6734 0.0441
-3.500 0.0269 0.01597 0.00869 -0.0678 0.6719 0.0166
-3.250 0.0539 0.01519 0.00788 -0.0675 0.6701 0.0159
-3.000 0.0801 0.01437 0.00706 -0.0672 0.6684 0.0155
-2.750 0.1061 0.01369 0.00637 -0.0669 0.6664 0.0154
-2.500 0.1324 0.01317 0.00584 -0.0667 0.6642 0.0155
-2.250 0.1594 0.01277 0.00541 -0.0666 0.6620 0.0162
-2.000 0.1860 0.01231 0.00492 -0.0665 0.6600 0.0172
-1.750 0.2137 0.01204 0.00462 -0.0665 0.6581 0.0192
-1.500 0.2416 0.01183 0.00437 -0.0666 0.6562 0.0231
-1.250 0.2672 0.01116 0.00411 -0.0666 0.6542 0.1499
-1.000 0.2795 0.00920 0.00435 -0.0647 0.6522 0.7704
-0.750 0.3046 0.00979 0.00497 -0.0634 0.6496 0.8164
-0.500 0.3246 0.01045 0.00569 -0.0604 0.6471 0.8395
-0.250 0.3444 0.01091 0.00616 -0.0576 0.6448 0.8586
0.000 0.3638 0.01110 0.00634 -0.0550 0.6426 0.8709
0.250 0.3879 0.01113 0.00631 -0.0538 0.6405 0.8781
0.500 0.4134 0.01121 0.00633 -0.0532 0.6383 0.8829
0.750 0.4417 0.01119 0.00630 -0.0536 0.6357 0.8857
1.000 0.4714 0.01116 0.00625 -0.0543 0.6328 0.8875
1.250 0.5016 0.01114 0.00618 -0.0551 0.6301 0.8888
1.500 0.5296 0.01102 0.00603 -0.0553 0.6275 0.8899
1.750 0.5581 0.01096 0.00591 -0.0555 0.6252 0.8911
2.000 0.5868 0.01096 0.00587 -0.0559 0.6226 0.8921
2.250 0.6148 0.01090 0.00585 -0.0563 0.6192 0.8931
2.500 0.6432 0.01085 0.00580 -0.0566 0.6158 0.8944
2.750 0.6722 0.01079 0.00572 -0.0571 0.6127 0.8956
3.000 0.7019 0.01075 0.00563 -0.0577 0.6099 0.8965
3.250 0.7310 0.01076 0.00564 -0.0582 0.6068 0.8974
3.500 0.7596 0.01073 0.00565 -0.0587 0.6029 0.8985
3.750 0.7887 0.01069 0.00562 -0.0593 0.5991 0.8997
4.000 0.8184 0.01066 0.00556 -0.0599 0.5958 0.9006
4.250 0.8480 0.01067 0.00557 -0.0606 0.5922 0.9014
4.500 0.8765 0.01066 0.00561 -0.0611 0.5875 0.9021
4.750 0.9059 0.01063 0.00559 -0.0618 0.5830 0.9028
5.000 0.9343 0.01057 0.00550 -0.0621 0.5789 0.9036
5.250 0.9606 0.01050 0.00553 -0.0621 0.5723 0.9047
5.500 0.9880 0.01041 0.00542 -0.0622 0.5651 0.9057
5.750 1.0147 0.01037 0.00544 -0.0624 0.5562 0.9066
6.000 1.0421 0.01038 0.00543 -0.0626 0.5495 0.9074
6.250 1.0691 0.01041 0.00554 -0.0628 0.5417 0.9083
6.500 1.0959 0.01046 0.00557 -0.0630 0.5338 0.9091
6.750 1.1223 0.01052 0.00570 -0.0631 0.5241 0.9101
7.000 1.1482 0.01062 0.00582 -0.0632 0.5146 0.9113
7.250 1.1732 0.01075 0.00595 -0.0631 0.5032 0.9125
7.500 1.1976 0.01092 0.00613 -0.0629 0.4901 0.9135
7.750 1.2213 0.01113 0.00634 -0.0627 0.4761 0.9145
8.000 1.2435 0.01141 0.00660 -0.0622 0.4604 0.9155
8.250 1.2641 0.01175 0.00692 -0.0615 0.4410 0.9165
8.500 1.2796 0.01221 0.00730 -0.0600 0.4178 0.9177
8.750 1.2904 0.01275 0.00776 -0.0576 0.3923 0.9196
9.000 1.2949 0.01337 0.00830 -0.0543 0.3701 0.9220
9.250 1.2995 0.01405 0.00893 -0.0511 0.3507 0.9242
9.500 1.3036 0.01489 0.00975 -0.0483 0.3324 0.9266
9.750 1.3058 0.01598 0.01078 -0.0456 0.3135 0.9291
10.000 1.3083 0.01723 0.01198 -0.0433 0.2959 0.9315
10.250 1.3116 0.01850 0.01323 -0.0413 0.2781 0.9346
10.500 1.3141 0.01992 0.01462 -0.0393 0.2597 0.9385
10.750 1.3165 0.02145 0.01610 -0.0375 0.2415 0.9423
11.000 1.3182 0.02315 0.01776 -0.0359 0.2231 0.9467
11.250 1.3229 0.02488 0.01945 -0.0350 0.2047 0.9529
11.750 1.3345 0.02863 0.02310 -0.0342 0.1689 1.0000
12.000 1.3395 0.03038 0.02483 -0.0334 0.1565 1.0000
12.250 1.3427 0.03230 0.02669 -0.0325 0.1428 1.0000
12.500 1.3489 0.03403 0.02843 -0.0319 0.1342 1.0000
13.000 1.3598 0.03777 0.03213 -0.0307 0.1141 1.0000
13.250 1.3662 0.03964 0.03400 -0.0303 0.1050 1.0000
13.500 1.3706 0.04171 0.03606 -0.0298 0.0960 1.0000
13.750 1.3755 0.04380 0.03812 -0.0294 0.0862 1.0000
14.000 1.3795 0.04603 0.04034 -0.0291 0.0762 1.0000
14.250 1.3828 0.04835 0.04265 -0.0288 0.0671 1.0000
14.500 1.3851 0.05084 0.04513 -0.0286 0.0599 1.0000
14.750 1.3871 0.05342 0.04771 -0.0285 0.0547 1.0000
15.000 1.3913 0.05583 0.05017 -0.0285 0.0504 1.0000
15.250 1.3944 0.05840 0.05279 -0.0285 0.0473 1.0000
15.500 1.3943 0.06139 0.05580 -0.0286 0.0441 1.0000
15.750 1.3985 0.06397 0.05846 -0.0288 0.0422 1.0000
16.000 1.4034 0.06647 0.06104 -0.0291 0.0400 1.0000
16.250 1.4054 0.06937 0.06399 -0.0295 0.0379 1.0000
16.500 1.4034 0.07283 0.06750 -0.0300 0.0356 1.0000
16.750 1.4086 0.07541 0.07017 -0.0305 0.0340 1.0000
17.000 1.4122 0.07826 0.07312 -0.0311 0.0327 1.0000
17.250 1.4145 0.08131 0.07624 -0.0318 0.0310 1.0000
17.500 1.4128 0.08496 0.07993 -0.0326 0.0290 1.0000
17.750 1.4139 0.08827 0.08333 -0.0335 0.0276 1.0000
18.000 1.4185 0.09111 0.08627 -0.0344 0.0257 1.0000
18.250 1.4174 0.09482 0.09002 -0.0356 0.0233 1.0000
18.500 1.4183 0.09829 0.09358 -0.0367 0.0203 1.0000
18.750 1.4147 0.10250 0.09782 -0.0381 0.0163 1.0000
19.000 1.4093 0.10701 0.10238 -0.0398 0.0138 1.0000
19.250 1.4005 0.11217 0.10759 -0.0417 0.0107 1.0000
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Polar data table (+)
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