BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Reynolds number: 100,000 Max Cl/Cd: 39.68 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v13009-il-100000-n5.txt Download as CSV file: xf-v13009-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V(1.95)3009-1.25 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 -0.6013 0.08779 0.08260 -0.0050 1.0000 0.0391
-8.750 -0.6077 0.08155 0.07639 -0.0103 1.0000 0.0384
-8.500 -0.6192 0.07485 0.06966 -0.0158 1.0000 0.0376
-8.250 -0.6280 0.06821 0.06291 -0.0195 1.0000 0.0369
-8.000 -0.6346 0.06154 0.05602 -0.0220 1.0000 0.0362
-7.750 -0.6377 0.05506 0.04922 -0.0231 1.0000 0.0357
-7.500 -0.6350 0.04952 0.04330 -0.0232 1.0000 0.0355
-7.250 -0.6274 0.04499 0.03840 -0.0226 1.0000 0.0355
-7.000 -0.6159 0.04125 0.03429 -0.0218 1.0000 0.0358
-6.750 -0.6016 0.03814 0.03084 -0.0209 1.0000 0.0363
-6.500 -0.5845 0.03577 0.02817 -0.0199 1.0000 0.0375
-6.250 -0.5669 0.03322 0.02523 -0.0188 1.0000 0.0390
-6.000 -0.5483 0.03057 0.02211 -0.0175 1.0000 0.0402
-5.750 -0.5279 0.02818 0.01925 -0.0163 1.0000 0.0411
-5.500 -0.5062 0.02616 0.01688 -0.0151 1.0000 0.0420
-5.250 -0.4842 0.02477 0.01543 -0.0143 1.0000 0.0432
-5.000 -0.4616 0.02362 0.01418 -0.0133 1.0000 0.0448
-4.750 -0.4386 0.02261 0.01304 -0.0124 1.0000 0.0476
-4.500 -0.4151 0.02161 0.01178 -0.0113 1.0000 0.0511
-4.250 -0.3928 0.02056 0.01082 -0.0104 1.0000 0.0539
-4.000 -0.3699 0.01970 0.00995 -0.0094 1.0000 0.0574
-3.750 -0.3469 0.01897 0.00910 -0.0084 1.0000 0.0628
-3.500 -0.3250 0.01824 0.00849 -0.0074 1.0000 0.0685
-3.250 -0.3026 0.01766 0.00785 -0.0063 1.0000 0.0756
-3.000 -0.2812 0.01703 0.00733 -0.0053 1.0000 0.0832
-2.750 -0.2595 0.01651 0.00682 -0.0042 1.0000 0.0919
-2.500 -0.2377 0.01609 0.00643 -0.0032 1.0000 0.1016
-2.250 -0.2161 0.01567 0.00609 -0.0023 1.0000 0.1129
-2.000 -0.1816 0.01523 0.00571 -0.0039 0.9936 0.1316
-1.750 -0.1412 0.01460 0.00534 -0.0068 0.9823 0.1746
-1.500 -0.1090 0.01260 0.00509 -0.0085 0.9710 0.5559
-1.250 -0.0774 0.01198 0.00527 -0.0077 0.9584 0.7798
-1.000 -0.0344 0.01191 0.00537 -0.0091 0.9470 0.8831
-0.750 0.0210 0.01195 0.00537 -0.0136 0.9344 0.9461
-0.500 0.1099 0.01192 0.00520 -0.0251 0.9233 1.0000
-0.250 0.1464 0.01180 0.00494 -0.0266 0.8895 1.0000
0.000 0.1768 0.01172 0.00470 -0.0267 0.8534 1.0000
0.250 0.2020 0.01170 0.00451 -0.0257 0.8155 1.0000
0.500 0.2257 0.01173 0.00435 -0.0244 0.7783 1.0000
0.750 0.2491 0.01179 0.00423 -0.0232 0.7431 1.0000
1.000 0.2726 0.01187 0.00416 -0.0220 0.7096 1.0000
1.250 0.2965 0.01198 0.00411 -0.0210 0.6753 1.0000
1.500 0.3202 0.01212 0.00408 -0.0199 0.6392 1.0000
1.750 0.3438 0.01230 0.00407 -0.0188 0.6024 1.0000
2.000 0.3674 0.01251 0.00410 -0.0178 0.5657 1.0000
2.250 0.3909 0.01275 0.00415 -0.0167 0.5303 1.0000
2.500 0.4142 0.01302 0.00425 -0.0157 0.4942 1.0000
2.750 0.4376 0.01331 0.00437 -0.0148 0.4561 1.0000
3.000 0.4608 0.01365 0.00451 -0.0138 0.4180 1.0000
3.250 0.4839 0.01402 0.00469 -0.0129 0.3830 1.0000
3.500 0.5073 0.01441 0.00493 -0.0120 0.3529 1.0000
3.750 0.5307 0.01482 0.00520 -0.0112 0.3250 1.0000
4.000 0.5543 0.01524 0.00549 -0.0104 0.2994 1.0000
4.250 0.5777 0.01569 0.00581 -0.0096 0.2774 1.0000
4.500 0.6015 0.01612 0.00615 -0.0089 0.2588 1.0000
4.750 0.6254 0.01656 0.00651 -0.0083 0.2434 1.0000
5.000 0.6493 0.01701 0.00690 -0.0076 0.2306 1.0000
5.250 0.6735 0.01744 0.00734 -0.0070 0.2185 1.0000
5.500 0.6977 0.01789 0.00779 -0.0063 0.2077 1.0000
5.750 0.7215 0.01838 0.00825 -0.0057 0.1977 1.0000
6.000 0.7451 0.01890 0.00876 -0.0051 0.1879 1.0000
6.250 0.7691 0.01940 0.00932 -0.0045 0.1780 1.0000
6.500 0.7925 0.01999 0.00989 -0.0038 0.1687 1.0000
6.750 0.8159 0.02056 0.01050 -0.0032 0.1589 1.0000
7.000 0.8393 0.02116 0.01120 -0.0026 0.1493 1.0000
7.250 0.8620 0.02180 0.01181 -0.0019 0.1404 1.0000
7.500 0.8855 0.02236 0.01252 -0.0013 0.1307 1.0000
7.750 0.9083 0.02300 0.01323 -0.0006 0.1222 1.0000
8.000 0.9306 0.02361 0.01389 0.0000 0.1147 1.0000
8.250 0.9531 0.02436 0.01477 0.0007 0.1073 1.0000
8.500 0.9743 0.02507 0.01547 0.0014 0.1014 1.0000
8.750 0.9960 0.02593 0.01649 0.0022 0.0951 1.0000
9.000 1.0164 0.02679 0.01739 0.0030 0.0903 1.0000
9.250 1.0364 0.02790 0.01861 0.0038 0.0863 1.0000
9.500 1.0561 0.02902 0.01989 0.0047 0.0821 1.0000
9.750 1.0749 0.03009 0.02101 0.0056 0.0785 1.0000
10.000 1.0926 0.03141 0.02244 0.0065 0.0754 1.0000
10.250 1.1102 0.03282 0.02411 0.0075 0.0722 1.0000
10.500 1.1267 0.03427 0.02574 0.0085 0.0696 1.0000
10.750 1.1424 0.03567 0.02725 0.0095 0.0674 1.0000
11.000 1.1573 0.03722 0.02881 0.0105 0.0653 1.0000
11.250 1.1682 0.03915 0.03111 0.0118 0.0632 1.0000
11.500 1.1768 0.04117 0.03346 0.0131 0.0611 1.0000
11.750 1.1837 0.04326 0.03579 0.0145 0.0594 1.0000
12.000 1.1889 0.04523 0.03795 0.0159 0.0578 1.0000
12.250 1.1928 0.04698 0.03979 0.0174 0.0564 1.0000
12.500 1.1981 0.04881 0.04162 0.0186 0.0550 1.0000
12.750 1.1883 0.05193 0.04504 0.0197 0.0540 1.0000
13.000 1.1729 0.05592 0.04936 0.0196 0.0532 1.0000
13.250 1.1538 0.06093 0.05467 0.0179 0.0526 1.0000
13.500 1.1298 0.06737 0.06139 0.0143 0.0523 1.0000
13.750 1.0973 0.07618 0.07046 0.0084 0.0524 1.0000
14.000 1.0490 0.08933 0.08384 -0.0010 0.0533 1.0000
14.250 0.8978 0.13019 0.12474 -0.0263 0.0551 1.0000
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Polar data table (+)
Polar graphs
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