AH 93-156 (ah93156-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-156 (ah93156-il) Reynolds number: 500,000 Max Cl/Cd: 103.07 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93156-il-500000.txt Download as CSV file: xf-ah93156-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-156
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3084 0.06903 0.06583 -0.1120 0.8187 0.0205
-12.000 -0.3671 0.05389 0.05059 -0.1230 0.8156 0.0198
-11.750 -0.3991 0.04815 0.04470 -0.1254 0.8120 0.0197
-11.500 -0.4292 0.04392 0.04028 -0.1245 0.8086 0.0195
-11.250 -0.4663 0.03973 0.03580 -0.1209 0.8053 0.0196
-11.000 -0.4931 0.03650 0.03233 -0.1163 0.8021 0.0193
-10.750 -0.5124 0.03410 0.02969 -0.1112 0.7986 0.0195
-10.500 -0.5279 0.03166 0.02695 -0.1060 0.7955 0.0196
-10.250 -0.5309 0.02938 0.02435 -0.1024 0.7930 0.0196
-10.000 -0.5270 0.02758 0.02221 -0.0994 0.7907 0.0201
-9.750 -0.5166 0.02629 0.02064 -0.0972 0.7886 0.0203
-9.500 -0.5071 0.02427 0.01833 -0.0950 0.7866 0.0207
-9.250 -0.4915 0.02263 0.01657 -0.0937 0.7843 0.0213
-9.000 -0.4720 0.02190 0.01580 -0.0927 0.7819 0.0220
-8.750 -0.4515 0.02132 0.01513 -0.0919 0.7797 0.0227
-8.500 -0.4302 0.02065 0.01435 -0.0911 0.7778 0.0235
-8.250 -0.4082 0.01997 0.01352 -0.0903 0.7760 0.0244
-8.000 -0.3853 0.01935 0.01275 -0.0896 0.7743 0.0251
-7.750 -0.3633 0.01808 0.01133 -0.0890 0.7725 0.0261
-7.500 -0.3408 0.01741 0.01068 -0.0884 0.7706 0.0272
-7.250 -0.3175 0.01696 0.01020 -0.0879 0.7684 0.0284
-7.000 -0.2935 0.01655 0.00973 -0.0874 0.7663 0.0297
-6.750 -0.2687 0.01628 0.00939 -0.0870 0.7644 0.0310
-6.500 -0.2470 0.01538 0.00845 -0.0862 0.7626 0.0329
-6.250 -0.2227 0.01502 0.00807 -0.0857 0.7608 0.0347
-6.000 -0.1980 0.01469 0.00768 -0.0853 0.7590 0.0367
-5.750 -0.1729 0.01446 0.00737 -0.0850 0.7572 0.0386
-5.500 -0.1512 0.01393 0.00689 -0.0841 0.7555 0.0420
-5.250 -0.1268 0.01368 0.00663 -0.0837 0.7534 0.0451
-5.000 -0.1031 0.01335 0.00628 -0.0831 0.7512 0.0484
-4.750 -0.0790 0.01304 0.00599 -0.0826 0.7491 0.0537
-4.500 -0.0540 0.01279 0.00570 -0.0822 0.7472 0.0592
-4.250 -0.0290 0.01252 0.00545 -0.0818 0.7454 0.0671
-4.000 -0.0040 0.01224 0.00520 -0.0815 0.7438 0.0786
-3.750 0.0214 0.01204 0.00502 -0.0812 0.7420 0.0950
-3.500 0.0451 0.01178 0.00490 -0.0807 0.7400 0.1215
-3.250 0.0682 0.01147 0.00479 -0.0801 0.7378 0.1642
-3.000 0.0907 0.01110 0.00467 -0.0794 0.7354 0.2287
-2.750 0.1117 0.01062 0.00455 -0.0786 0.7331 0.3244
-2.500 0.1309 0.01001 0.00439 -0.0774 0.7310 0.4503
-2.250 0.1428 0.00904 0.00421 -0.0746 0.7290 0.6594
-2.000 0.1629 0.00911 0.00474 -0.0721 0.7272 0.7979
-1.750 0.1888 0.00940 0.00500 -0.0715 0.7250 0.8281
-1.500 0.2140 0.00966 0.00524 -0.0708 0.7224 0.8435
-1.250 0.2398 0.00998 0.00555 -0.0699 0.7196 0.8522
-1.000 0.2659 0.01018 0.00571 -0.0693 0.7169 0.8615
-0.750 0.2926 0.01041 0.00589 -0.0686 0.7144 0.8694
-0.500 0.3195 0.01058 0.00600 -0.0680 0.7122 0.8767
-0.250 0.3455 0.01079 0.00618 -0.0673 0.7098 0.8824
0.000 0.3681 0.01093 0.00634 -0.0660 0.7067 0.8905
0.250 0.3923 0.01113 0.00653 -0.0646 0.7037 0.8987
0.500 0.4182 0.01124 0.00663 -0.0636 0.7010 0.9077
0.750 0.4431 0.01134 0.00669 -0.0626 0.6986 0.9177
1.000 0.4822 0.01136 0.00666 -0.0645 0.6964 0.9219
1.250 0.5082 0.01135 0.00666 -0.0643 0.6933 0.9259
1.500 0.5214 0.01129 0.00661 -0.0616 0.6896 0.9309
1.750 0.5503 0.01114 0.00645 -0.0620 0.6864 0.9323
2.000 0.5808 0.01103 0.00629 -0.0627 0.6836 0.9335
2.250 0.6114 0.01095 0.00617 -0.0635 0.6810 0.9347
2.500 0.6351 0.01090 0.00616 -0.0629 0.6771 0.9369
2.750 0.6579 0.01081 0.00608 -0.0621 0.6731 0.9391
3.000 0.6808 0.01070 0.00596 -0.0613 0.6694 0.9416
3.250 0.7041 0.01062 0.00584 -0.0607 0.6662 0.9436
3.500 0.7258 0.01051 0.00578 -0.0597 0.6615 0.9452
3.750 0.7520 0.01038 0.00567 -0.0596 0.6565 0.9467
4.000 0.7798 0.01028 0.00555 -0.0598 0.6523 0.9479
4.250 0.8037 0.01022 0.00552 -0.0593 0.6473 0.9493
4.500 0.8266 0.01014 0.00547 -0.0585 0.6414 0.9511
4.750 0.8526 0.01005 0.00536 -0.0584 0.6362 0.9527
5.000 0.8703 0.00999 0.00536 -0.0566 0.6290 0.9547
5.250 0.8925 0.00992 0.00527 -0.0557 0.6224 0.9562
5.500 0.9124 0.00986 0.00526 -0.0545 0.6146 0.9580
5.750 0.9368 0.00982 0.00520 -0.0541 0.6068 0.9592
6.000 0.9575 0.00981 0.00524 -0.0530 0.5972 0.9607
6.250 0.9791 0.00982 0.00526 -0.0521 0.5878 0.9621
6.500 0.9990 0.00986 0.00529 -0.0508 0.5770 0.9639
6.750 1.0158 0.00992 0.00537 -0.0490 0.5646 0.9662
7.000 1.0306 0.01000 0.00545 -0.0468 0.5520 0.9683
7.250 1.0420 0.01011 0.00555 -0.0440 0.5380 0.9705
7.500 1.0587 0.01034 0.00577 -0.0425 0.5229 0.9727
7.750 1.0763 0.01067 0.00607 -0.0412 0.5070 0.9753
8.000 1.0929 0.01108 0.00645 -0.0400 0.4900 0.9778
8.250 1.1090 0.01161 0.00693 -0.0389 0.4723 0.9803
8.500 1.1262 0.01224 0.00753 -0.0383 0.4541 0.9828
8.750 1.1450 0.01303 0.00827 -0.0383 0.4323 0.9853
9.000 1.1612 0.01398 0.00915 -0.0381 0.4105 0.9890
9.250 1.1763 0.01496 0.01008 -0.0377 0.3882 0.9988
9.500 1.1780 0.01589 0.01095 -0.0346 0.3692 1.0000
9.750 1.1811 0.01687 0.01187 -0.0318 0.3513 1.0000
10.000 1.1848 0.01796 0.01290 -0.0293 0.3327 1.0000
10.250 1.1913 0.01903 0.01391 -0.0273 0.3128 1.0000
10.500 1.1941 0.02037 0.01515 -0.0251 0.2891 1.0000
10.750 1.2002 0.02159 0.01630 -0.0233 0.2696 1.0000
11.000 1.2030 0.02305 0.01764 -0.0213 0.2452 1.0000
11.250 1.2059 0.02455 0.01904 -0.0194 0.2213 1.0000
11.500 1.2087 0.02613 0.02050 -0.0176 0.1988 1.0000
11.750 1.2114 0.02779 0.02204 -0.0159 0.1737 1.0000
12.000 1.2145 0.02947 0.02362 -0.0144 0.1519 1.0000
12.250 1.2159 0.03133 0.02534 -0.0128 0.1283 1.0000
12.500 1.2172 0.03327 0.02715 -0.0113 0.1049 1.0000
12.750 1.2193 0.03520 0.02899 -0.0100 0.0862 1.0000
13.000 1.2208 0.03725 0.03094 -0.0088 0.0681 1.0000
13.250 1.2215 0.03942 0.03302 -0.0076 0.0531 1.0000
13.500 1.2229 0.04159 0.03515 -0.0065 0.0410 1.0000
13.750 1.2241 0.04387 0.03738 -0.0055 0.0322 1.0000
14.000 1.2256 0.04618 0.03970 -0.0047 0.0262 1.0000
14.250 1.2276 0.04850 0.04205 -0.0040 0.0225 1.0000
14.500 1.2295 0.05091 0.04448 -0.0034 0.0198 1.0000
14.750 1.2309 0.05344 0.04709 -0.0029 0.0176 1.0000
15.000 1.2329 0.05597 0.04967 -0.0025 0.0161 1.0000
15.250 1.2296 0.05910 0.05287 -0.0021 0.0149 1.0000
15.500 1.2346 0.06142 0.05527 -0.0020 0.0141 1.0000
15.750 1.2343 0.06440 0.05834 -0.0020 0.0133 1.0000
16.000 1.2363 0.06716 0.06115 -0.0021 0.0125 1.0000
16.250 1.2301 0.07094 0.06501 -0.0022 0.0120 1.0000
16.500 1.2266 0.07448 0.06866 -0.0025 0.0115 1.0000
16.750 1.2256 0.07782 0.07209 -0.0028 0.0112 1.0000
17.000 1.2241 0.08127 0.07563 -0.0034 0.0110 1.0000
17.250 1.2237 0.08463 0.07909 -0.0040 0.0107 1.0000
17.500 1.2217 0.08823 0.08278 -0.0048 0.0102 1.0000
17.750 1.2200 0.09184 0.08648 -0.0056 0.0103 1.0000
18.000 1.2177 0.09560 0.09031 -0.0065 0.0099 1.0000
18.250 1.2145 0.09950 0.09428 -0.0076 0.0097 1.0000
18.500 1.2128 0.10323 0.09809 -0.0087 0.0096 1.0000
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Polar data table (+)
Polar graphs
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