AH 83-150 Q (ah83150q-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 83-150 Q (ah83150q-il) Reynolds number: 100,000 Max Cl/Cd: 35.36 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah83150q-il-100000-n5.txt Download as CSV file: xf-ah83150q-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2074 0.09890 0.09355 -0.0639 0.7835 0.0555
-9.500 -0.2061 0.09547 0.09012 -0.0659 0.7807 0.0569
-9.250 -0.2182 0.09135 0.08607 -0.0722 0.7771 0.0597
-9.000 -0.2375 0.08630 0.08105 -0.0799 0.7732 0.0602
-8.750 -0.2533 0.08294 0.07763 -0.0824 0.7697 0.0604
-8.250 -0.1911 0.05675 0.05161 -0.0830 0.7574 0.0321
-7.750 -0.2503 0.06269 0.05710 -0.0847 0.7582 0.0326
-7.250 -0.2520 0.05428 0.04813 -0.0837 0.7523 0.0252
-7.000 -0.2436 0.05174 0.04546 -0.0831 0.7501 0.0248
-6.750 -0.2352 0.04899 0.04251 -0.0824 0.7475 0.0242
-6.500 -0.2248 0.04621 0.03949 -0.0818 0.7442 0.0235
-6.250 -0.2131 0.04334 0.03631 -0.0809 0.7409 0.0228
-6.000 -0.1995 0.04041 0.03298 -0.0797 0.7381 0.0221
-5.750 -0.1833 0.03754 0.02960 -0.0784 0.7358 0.0214
-5.500 -0.1640 0.03499 0.02639 -0.0769 0.7338 0.0207
-5.250 -0.1423 0.03318 0.02423 -0.0762 0.7312 0.0205
-5.000 -0.1195 0.03163 0.02239 -0.0757 0.7278 0.0205
-4.750 -0.0959 0.03011 0.02064 -0.0752 0.7248 0.0207
-4.500 -0.0717 0.02890 0.01929 -0.0748 0.7222 0.0214
-4.250 -0.0467 0.02795 0.01821 -0.0745 0.7200 0.0228
-4.000 -0.0206 0.02698 0.01702 -0.0739 0.7181 0.0244
-3.750 0.0050 0.02616 0.01601 -0.0734 0.7154 0.0254
-3.500 0.0283 0.02529 0.01517 -0.0729 0.7118 0.0261
-3.250 0.0514 0.02461 0.01450 -0.0723 0.7088 0.0271
-3.000 0.0746 0.02405 0.01389 -0.0716 0.7062 0.0284
-2.750 0.0982 0.02352 0.01324 -0.0709 0.7040 0.0303
-2.500 0.1225 0.02302 0.01265 -0.0702 0.7020 0.0336
-2.250 0.1450 0.02284 0.01244 -0.0696 0.6986 0.0403
-2.000 0.1669 0.02264 0.01228 -0.0689 0.6949 0.0512
-1.750 0.1781 0.02097 0.01209 -0.0669 0.6917 0.3607
-1.500 0.1721 0.02120 0.01390 -0.0570 0.6891 0.8028
-1.250 0.2030 0.02247 0.01512 -0.0506 0.6876 0.9100
-1.000 0.2445 0.02242 0.01479 -0.0527 0.6860 0.9214
-0.750 0.2693 0.02271 0.01495 -0.0529 0.6818 0.9294
-0.500 0.2965 0.02287 0.01498 -0.0534 0.6778 0.9338
-0.250 0.3277 0.02289 0.01485 -0.0545 0.6748 0.9372
0.000 0.3555 0.02286 0.01467 -0.0548 0.6724 0.9406
0.250 0.3793 0.02279 0.01446 -0.0541 0.6703 0.9443
0.500 0.3992 0.02324 0.01489 -0.0539 0.6649 0.9476
0.750 0.4251 0.02344 0.01502 -0.0543 0.6608 0.9501
1.000 0.4521 0.02345 0.01495 -0.0545 0.6578 0.9524
1.250 0.4798 0.02338 0.01477 -0.0547 0.6556 0.9546
1.500 0.4949 0.02375 0.01513 -0.0532 0.6509 0.9581
1.750 0.5153 0.02416 0.01554 -0.0529 0.6455 0.9609
2.000 0.5446 0.02418 0.01550 -0.0536 0.6424 0.9626
2.250 0.5742 0.02407 0.01533 -0.0541 0.6401 0.9639
2.750 0.6123 0.02496 0.01626 -0.0530 0.6291 0.9701
3.000 0.6380 0.02488 0.01616 -0.0528 0.6262 0.9722
3.250 0.6695 0.02469 0.01593 -0.0534 0.6241 0.9732
3.500 0.6840 0.02566 0.01700 -0.0531 0.6154 0.9768
3.750 0.7132 0.02562 0.01698 -0.0536 0.6119 0.9789
4.000 0.7451 0.02535 0.01669 -0.0542 0.6095 0.9804
4.500 0.7834 0.02624 0.01769 -0.0534 0.5969 0.9869
4.750 0.8172 0.02588 0.01737 -0.0543 0.5945 0.9886
5.250 0.8553 0.02671 0.01834 -0.0534 0.5814 0.9991
5.500 0.8852 0.02623 0.01787 -0.0533 0.5791 1.0000
5.750 0.8500 0.02764 0.01934 -0.0448 0.5674 1.0000
6.000 0.8808 0.02710 0.01886 -0.0448 0.5649 1.0000
6.500 0.8964 0.02796 0.01982 -0.0400 0.5505 1.0000
7.000 0.9263 0.02878 0.02078 -0.0379 0.5358 1.0000
7.500 0.9642 0.02937 0.02150 -0.0368 0.5208 1.0000
7.750 0.9690 0.03074 0.02294 -0.0356 0.5086 1.0000
8.250 1.0204 0.03020 0.02255 -0.0351 0.4914 1.0000
8.500 1.0330 0.03101 0.02342 -0.0343 0.4784 1.0000
8.750 1.0491 0.03159 0.02408 -0.0337 0.4663 1.0000
9.000 1.0717 0.03168 0.02424 -0.0333 0.4554 1.0000
9.250 1.1019 0.03116 0.02376 -0.0332 0.4458 1.0000
9.500 1.1169 0.03191 0.02459 -0.0326 0.4324 1.0000
9.750 1.1340 0.03249 0.02522 -0.0320 0.4189 1.0000
10.000 1.1514 0.03305 0.02582 -0.0314 0.4047 1.0000
10.250 1.1680 0.03368 0.02647 -0.0308 0.3897 1.0000
10.500 1.1829 0.03445 0.02727 -0.0300 0.3741 1.0000
10.750 1.1962 0.03535 0.02817 -0.0293 0.3577 1.0000
11.250 1.2150 0.03787 0.03068 -0.0275 0.3233 1.0000
11.500 1.2201 0.03953 0.03233 -0.0266 0.3047 1.0000
11.750 1.2244 0.04129 0.03405 -0.0257 0.2855 1.0000
12.000 1.2271 0.04319 0.03590 -0.0248 0.2663 1.0000
12.250 1.2285 0.04534 0.03802 -0.0240 0.2477 1.0000
12.500 1.2301 0.04757 0.04023 -0.0234 0.2302 1.0000
12.750 1.2317 0.04989 0.04252 -0.0229 0.2138 1.0000
13.000 1.2333 0.05227 0.04489 -0.0224 0.1990 1.0000
13.250 1.2353 0.05471 0.04733 -0.0221 0.1856 1.0000
13.500 1.2372 0.05723 0.04985 -0.0219 0.1733 1.0000
13.750 1.2388 0.05983 0.05248 -0.0218 0.1624 1.0000
14.000 1.2401 0.06255 0.05521 -0.0218 0.1519 1.0000
14.250 1.2425 0.06524 0.05798 -0.0218 0.1420 1.0000
14.500 1.2439 0.06806 0.06084 -0.0220 0.1334 1.0000
14.750 1.2444 0.07107 0.06389 -0.0222 0.1250 1.0000
15.000 1.2464 0.07400 0.06692 -0.0225 0.1170 1.0000
15.250 1.2451 0.07734 0.07024 -0.0230 0.1100 1.0000
15.500 1.2473 0.08038 0.07345 -0.0235 0.1025 1.0000
15.750 1.2465 0.08374 0.07682 -0.0241 0.0970 1.0000
16.000 1.2486 0.08689 0.08015 -0.0247 0.0907 1.0000
16.250 1.2474 0.09043 0.08372 -0.0255 0.0858 1.0000
16.500 1.2494 0.09364 0.08707 -0.0263 0.0809 1.0000
16.750 1.2493 0.09717 0.09070 -0.0272 0.0765 1.0000
17.000 1.2498 0.10054 0.09406 -0.0282 0.0731 1.0000
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Polar data table (+)
Polar graphs
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