BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il) Reynolds number: 100,000 Max Cl/Cd: 41.21 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v23010-il-100000-n5.txt Download as CSV file: xf-v23010-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL V23010-1.58 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5080 0.09222 0.08696 -0.0115 1.0000 0.0687
-8.750 -0.5156 0.08736 0.08215 -0.0158 1.0000 0.0702
-8.500 -0.5388 0.08168 0.07649 -0.0224 1.0000 0.0713
-8.250 -0.5728 0.07827 0.07284 -0.0250 1.0000 0.0723
-8.000 -0.5858 0.07562 0.06989 -0.0251 1.0000 0.0727
-7.750 -0.5704 0.06959 0.06407 -0.0253 1.0000 0.0736
-7.500 -0.5569 0.06601 0.06058 -0.0248 1.0000 0.0748
-7.250 -0.5472 0.06311 0.05769 -0.0242 1.0000 0.0766
-7.000 -0.5404 0.06029 0.05481 -0.0236 1.0000 0.0794
-6.750 -0.5483 0.05786 0.05183 -0.0228 1.0000 0.0867
-6.250 -0.5234 0.04763 0.04074 -0.0196 1.0000 0.0525
-6.000 -0.5070 0.04476 0.03798 -0.0187 1.0000 0.0497
-5.500 -0.4815 0.03906 0.03134 -0.0142 1.0000 0.0439
-5.250 -0.4657 0.03687 0.02905 -0.0128 1.0000 0.0435
-5.000 -0.4497 0.03488 0.02689 -0.0111 1.0000 0.0431
-4.750 -0.4334 0.03318 0.02490 -0.0092 1.0000 0.0435
-4.500 -0.4169 0.03170 0.02311 -0.0072 1.0000 0.0439
-4.250 -0.4001 0.03034 0.02147 -0.0052 1.0000 0.0441
-4.000 -0.3828 0.02885 0.01985 -0.0035 1.0000 0.0440
-3.750 -0.3654 0.02752 0.01840 -0.0019 1.0000 0.0438
-3.500 -0.3283 0.02592 0.01662 -0.0038 0.9920 0.0437
-3.250 -0.2858 0.02442 0.01492 -0.0067 0.9809 0.0437
-3.000 -0.2403 0.02301 0.01334 -0.0098 0.9659 0.0439
-2.750 -0.1942 0.02173 0.01194 -0.0129 0.9479 0.0442
-2.500 -0.1536 0.02043 0.01072 -0.0152 0.9278 0.0455
-2.250 -0.1186 0.01956 0.00990 -0.0164 0.9065 0.0474
-2.000 -0.0836 0.01875 0.00907 -0.0174 0.8869 0.0490
-1.750 -0.0505 0.01798 0.00830 -0.0179 0.8670 0.0500
-1.500 -0.0210 0.01736 0.00765 -0.0177 0.8449 0.0511
-1.250 0.0054 0.01685 0.00708 -0.0170 0.8190 0.0522
-1.000 0.0307 0.01633 0.00651 -0.0161 0.7920 0.0540
-0.750 0.0569 0.01598 0.00603 -0.0152 0.7661 0.0572
-0.500 0.0831 0.01575 0.00563 -0.0144 0.7403 0.0618
-0.250 0.1085 0.01546 0.00525 -0.0135 0.7138 0.0676
0.000 0.1338 0.01523 0.00491 -0.0125 0.6839 0.0769
0.250 0.1505 0.01327 0.00459 -0.0108 0.6525 0.5259
0.500 0.1796 0.01251 0.00492 -0.0085 0.6109 0.8679
0.750 0.2754 0.01305 0.00502 -0.0199 0.5331 0.9829
1.000 0.3195 0.01326 0.00484 -0.0233 0.4781 0.9964
1.250 0.3454 0.01348 0.00476 -0.0231 0.4395 1.0000
1.500 0.3649 0.01371 0.00474 -0.0217 0.4115 1.0000
1.750 0.3849 0.01396 0.00477 -0.0204 0.3893 1.0000
2.000 0.4055 0.01422 0.00485 -0.0191 0.3720 1.0000
2.250 0.4268 0.01447 0.00496 -0.0179 0.3585 1.0000
2.500 0.4484 0.01475 0.00511 -0.0168 0.3477 1.0000
2.750 0.4703 0.01503 0.00528 -0.0157 0.3375 1.0000
3.000 0.4926 0.01531 0.00546 -0.0146 0.3274 1.0000
3.250 0.5147 0.01562 0.00564 -0.0136 0.3178 1.0000
3.500 0.5375 0.01589 0.00587 -0.0126 0.3077 1.0000
3.750 0.5601 0.01621 0.00609 -0.0117 0.2989 1.0000
4.000 0.5830 0.01651 0.00635 -0.0107 0.2907 1.0000
4.250 0.6059 0.01687 0.00663 -0.0098 0.2842 1.0000
4.500 0.6293 0.01719 0.00697 -0.0090 0.2771 1.0000
4.750 0.6523 0.01758 0.00728 -0.0081 0.2710 1.0000
5.000 0.6759 0.01795 0.00767 -0.0073 0.2649 1.0000
5.250 0.6994 0.01833 0.00808 -0.0065 0.2589 1.0000
5.500 0.7227 0.01878 0.00846 -0.0057 0.2536 1.0000
5.750 0.7464 0.01918 0.00895 -0.0050 0.2472 1.0000
6.000 0.7698 0.01959 0.00940 -0.0042 0.2407 1.0000
6.250 0.7931 0.02007 0.00985 -0.0034 0.2349 1.0000
6.500 0.8165 0.02049 0.01041 -0.0027 0.2279 1.0000
6.750 0.8397 0.02096 0.01089 -0.0019 0.2221 1.0000
7.000 0.8630 0.02148 0.01150 -0.0012 0.2165 1.0000
7.250 0.8860 0.02200 0.01213 -0.0005 0.2102 1.0000
7.500 0.9090 0.02249 0.01261 0.0003 0.2050 1.0000
7.750 0.9315 0.02306 0.01337 0.0010 0.1987 1.0000
8.000 0.9540 0.02360 0.01400 0.0018 0.1929 1.0000
8.250 0.9766 0.02414 0.01453 0.0026 0.1887 1.0000
8.500 0.9982 0.02479 0.01544 0.0034 0.1822 1.0000
8.750 1.0195 0.02513 0.01583 0.0043 0.1757 1.0000
9.000 1.0397 0.02552 0.01638 0.0053 0.1672 1.0000
9.250 1.0595 0.02572 0.01659 0.0063 0.1592 1.0000
9.500 1.0792 0.02619 0.01726 0.0073 0.1505 1.0000
9.750 1.0982 0.02672 0.01786 0.0084 0.1439 1.0000
10.000 1.1168 0.02734 0.01862 0.0094 0.1367 1.0000
10.250 1.1340 0.02802 0.01940 0.0106 0.1301 1.0000
10.500 1.1501 0.02877 0.02027 0.0118 0.1227 1.0000
10.750 1.1647 0.02967 0.02128 0.0132 0.1154 1.0000
11.000 1.1768 0.03062 0.02230 0.0147 0.1079 1.0000
11.250 1.1882 0.03174 0.02363 0.0162 0.0994 1.0000
11.500 1.1957 0.03297 0.02495 0.0181 0.0918 1.0000
11.750 1.2002 0.03430 0.02642 0.0202 0.0843 1.0000
12.000 1.2011 0.03584 0.02808 0.0225 0.0780 1.0000
12.250 1.1987 0.03764 0.02995 0.0244 0.0733 1.0000
12.500 1.1947 0.03985 0.03227 0.0257 0.0692 1.0000
12.750 1.1882 0.04253 0.03507 0.0263 0.0659 1.0000
13.000 1.1783 0.04587 0.03849 0.0260 0.0637 1.0000
13.250 1.1668 0.04985 0.04257 0.0248 0.0619 1.0000
13.500 1.1544 0.05445 0.04734 0.0229 0.0602 1.0000
13.750 1.1397 0.05978 0.05283 0.0203 0.0589 1.0000
14.000 1.1233 0.06574 0.05893 0.0170 0.0578 1.0000
14.250 1.1061 0.07208 0.06540 0.0136 0.0568 1.0000
14.500 1.0905 0.07826 0.07166 0.0103 0.0559 1.0000
14.750 1.0774 0.08399 0.07743 0.0074 0.0548 1.0000
15.000 1.0651 0.08965 0.08314 0.0046 0.0536 1.0000
15.250 1.0487 0.09643 0.09009 0.0011 0.0526 1.0000
15.500 1.0302 0.10387 0.09767 -0.0028 0.0515 1.0000
15.750 1.0109 0.11174 0.10569 -0.0069 0.0507 1.0000
16.000 0.9854 0.12133 0.11542 -0.0121 0.0499 1.0000
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Polar data table (+)
Polar graphs
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