AH 93-W-215 (ah93w215-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-W-215 (ah93w215-il) Reynolds number: 50,000 Max Cl/Cd: 6.39 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93w215-il-50000-n5.txt Download as CSV file: xf-ah93w215-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-215
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3836 0.10665 0.09895 -0.0627 1.0000 0.1196
-12.500 -0.5044 0.08272 0.07493 -0.0749 1.0000 0.1222
-12.250 -0.6019 0.06995 0.06202 -0.0793 1.0000 0.1220
-12.000 -0.6461 0.06197 0.05375 -0.0835 0.9626 0.1230
-11.750 -0.6501 0.05758 0.04909 -0.0870 0.9377 0.1254
-11.500 -0.6195 0.05574 0.04721 -0.0902 0.9224 0.1293
-11.250 -0.6115 0.05225 0.04338 -0.0936 0.9074 0.1332
-11.000 -0.6110 0.04852 0.03909 -0.0962 0.8933 0.1370
-10.750 -0.5679 0.04724 0.03787 -0.0998 0.8830 0.1420
-10.500 -0.5442 0.04502 0.03535 -0.1025 0.8726 0.1476
-10.250 -0.5284 0.04318 0.03322 -0.1033 0.8600 0.1525
-10.000 -0.4934 0.04197 0.03194 -0.1059 0.8514 0.1588
-9.750 -0.4834 0.04061 0.03028 -0.1051 0.8401 0.1644
-9.500 -0.4500 0.03950 0.02913 -0.1070 0.8328 0.1711
-9.250 -0.4376 0.03865 0.02815 -0.1058 0.8232 0.1775
-9.000 -0.4156 0.03766 0.02702 -0.1059 0.8155 0.1847
-8.750 -0.3955 0.03696 0.02626 -0.1055 0.8083 0.1925
-8.500 -0.3824 0.03624 0.02542 -0.1040 0.8004 0.2002
-8.250 -0.3584 0.03559 0.02476 -0.1040 0.7943 0.2093
-8.000 -0.3422 0.03497 0.02406 -0.1028 0.7882 0.2187
-7.750 -0.3287 0.03454 0.02365 -0.1011 0.7813 0.2281
-7.500 -0.3111 0.03399 0.02309 -0.1000 0.7755 0.2392
-7.250 -0.2912 0.03340 0.02240 -0.0993 0.7707 0.2527
-7.000 -0.2836 0.03318 0.02233 -0.0965 0.7640 0.2633
-6.750 -0.2715 0.03284 0.02203 -0.0944 0.7584 0.2770
-6.500 -0.2552 0.03243 0.02165 -0.0930 0.7537 0.2935
-6.250 -0.2398 0.03210 0.02137 -0.0914 0.7493 0.3118
-5.750 -0.2281 0.03197 0.02147 -0.0849 0.7375 0.3484
-5.500 -0.2118 0.03184 0.02146 -0.0830 0.7332 0.3724
-5.250 -0.1927 0.03176 0.02143 -0.0816 0.7297 0.4000
-5.000 -0.1963 0.03217 0.02197 -0.0766 0.7232 0.4194
-4.750 -0.1889 0.03240 0.02225 -0.0732 0.7178 0.4437
-4.500 -0.1702 0.03265 0.02255 -0.0713 0.7136 0.4693
-4.250 -0.1481 0.03283 0.02268 -0.0700 0.7103 0.4956
-4.000 -0.1509 0.03346 0.02337 -0.0650 0.7043 0.5128
-3.750 -0.1471 0.03399 0.02391 -0.0611 0.6986 0.5314
-3.500 -0.1309 0.03434 0.02423 -0.0588 0.6942 0.5516
-3.250 -0.1068 0.03462 0.02444 -0.0577 0.6908 0.5720
-3.000 -0.1027 0.03517 0.02497 -0.0538 0.6858 0.5881
-2.750 -0.1154 0.03591 0.02573 -0.0479 0.6788 0.6024
-2.500 -0.0966 0.03643 0.02624 -0.0459 0.6744 0.6182
-2.250 -0.0702 0.03675 0.02650 -0.0450 0.6711 0.6348
-2.000 -0.0401 0.03698 0.02664 -0.0447 0.6685 0.6518
-1.750 -0.0840 0.03832 0.02810 -0.0348 0.6584 0.6615
-1.500 -0.0683 0.03885 0.02861 -0.0326 0.6539 0.6757
-1.250 -0.0422 0.03910 0.02878 -0.0317 0.6507 0.6920
-1.000 -0.0130 0.03925 0.02883 -0.0313 0.6483 0.7090
-0.750 -0.0652 0.04101 0.03076 -0.0207 0.6369 0.7172
-0.500 -0.0495 0.04143 0.03113 -0.0187 0.6327 0.7327
-0.250 -0.0224 0.04155 0.03116 -0.0181 0.6298 0.7486
0.000 -0.0348 0.04298 0.03265 -0.0132 0.6220 0.7598
0.250 -0.0377 0.04391 0.03357 -0.0097 0.6153 0.7738
0.500 -0.0147 0.04418 0.03379 -0.0087 0.6115 0.7870
0.750 0.0174 0.04424 0.03376 -0.0089 0.6090 0.7989
1.250 0.0067 0.04660 0.03615 -0.0023 0.5942 0.8264
1.500 0.0363 0.04678 0.03627 -0.0025 0.5909 0.8390
1.750 0.0689 0.04673 0.03615 -0.0028 0.5885 0.8527
2.000 0.0463 0.04886 0.03835 0.0010 0.5777 0.8690
2.250 0.0782 0.04938 0.03884 -0.0003 0.5735 0.8817
2.500 0.1176 0.04961 0.03901 -0.0022 0.5706 0.8945
2.750 0.1239 0.05136 0.04081 -0.0023 0.5622 0.9100
3.000 0.1537 0.05237 0.04180 -0.0045 0.5565 0.9238
3.250 0.2010 0.05292 0.04231 -0.0085 0.5530 0.9345
3.500 0.2539 0.05323 0.04256 -0.0129 0.5505 0.9444
3.750 0.2616 0.05602 0.04542 -0.0154 0.5395 0.9578
4.000 0.3073 0.05671 0.04609 -0.0195 0.5353 0.9686
4.250 0.3579 0.05701 0.04635 -0.0237 0.5326 0.9801
4.500 0.3536 0.05979 0.04915 -0.0244 0.5221 1.0000
4.750 0.3515 0.05986 0.04913 -0.0210 0.5176 1.0000
5.000 0.3666 0.05973 0.04889 -0.0193 0.5146 1.0000
5.250 0.3393 0.06195 0.05104 -0.0154 0.5046 1.0000
5.500 0.3528 0.06251 0.05152 -0.0142 0.4998 1.0000
5.750 0.3763 0.06272 0.05164 -0.0136 0.4968 1.0000
6.000 0.3604 0.06518 0.05407 -0.0113 0.4870 1.0000
6.250 0.3769 0.06594 0.05476 -0.0106 0.4822 1.0000
6.500 0.4026 0.06623 0.05499 -0.0103 0.4791 1.0000
6.750 0.3893 0.06893 0.05769 -0.0086 0.4694 1.0000
7.000 0.4072 0.06974 0.05845 -0.0081 0.4645 1.0000
7.250 0.4336 0.07005 0.05871 -0.0079 0.4615 1.0000
7.500 0.4207 0.07300 0.06168 -0.0066 0.4516 1.0000
7.750 0.4395 0.07384 0.06249 -0.0062 0.4469 1.0000
8.000 0.4669 0.07409 0.06270 -0.0060 0.4439 1.0000
8.250 0.4528 0.07735 0.06598 -0.0050 0.4336 1.0000
8.500 0.4731 0.07812 0.06675 -0.0047 0.4292 1.0000
8.750 0.5009 0.07834 0.06695 -0.0045 0.4264 1.0000
9.000 0.4847 0.08198 0.07063 -0.0038 0.4155 1.0000
9.250 0.5063 0.08271 0.07135 -0.0036 0.4115 1.0000
9.500 0.5313 0.08314 0.07177 -0.0034 0.4083 1.0000
9.750 0.5161 0.08691 0.07560 -0.0030 0.3975 1.0000
10.000 0.5392 0.08750 0.07618 -0.0028 0.3937 1.0000
10.250 0.5356 0.09046 0.07918 -0.0026 0.3856 1.0000
10.500 0.5473 0.09204 0.08079 -0.0024 0.3794 1.0000
10.750 0.5720 0.09244 0.08121 -0.0021 0.3760 1.0000
11.000 0.5613 0.09622 0.08503 -0.0022 0.3666 1.0000
11.250 0.5776 0.09743 0.08626 -0.0021 0.3614 1.0000
11.500 0.6040 0.09758 0.08645 -0.0018 0.3582 1.0000
11.750 0.5881 0.10207 0.09099 -0.0022 0.3478 1.0000
12.000 0.6080 0.10290 0.09185 -0.0020 0.3434 1.0000
12.250 0.6304 0.10348 0.09246 -0.0018 0.3400 1.0000
12.500 0.6145 0.10816 0.09720 -0.0025 0.3295 1.0000
12.750 0.6361 0.10880 0.09788 -0.0023 0.3257 1.0000
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