BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL (vr7-il) Reynolds number: 100,000 Max Cl/Cd: 51.72 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr7-il-100000.txt Download as CSV file: xf-vr7-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-7 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3806 0.09679 0.09201 -0.0299 1.0000 0.1077
-9.000 -0.4039 0.09356 0.08893 -0.0360 1.0000 0.1114
-8.750 -0.4352 0.08986 0.08536 -0.0422 1.0000 0.1119
-8.500 -0.3826 0.08651 0.08194 -0.0334 1.0000 0.1188
-8.250 -0.3928 0.08326 0.07881 -0.0358 1.0000 0.1238
-8.000 -0.4297 0.07957 0.07525 -0.0411 1.0000 0.1259
-7.750 -0.4499 0.07567 0.07139 -0.0423 1.0000 0.1279
-7.500 -0.4157 0.07358 0.06943 -0.0370 1.0000 0.1346
-7.250 -0.4388 0.07108 0.06701 -0.0372 1.0000 0.1391
-7.000 -0.4716 0.07075 0.06681 -0.0318 1.0000 0.1392
-6.750 -0.4779 0.06730 0.06332 -0.0339 0.9940 0.1443
-6.500 -0.4490 0.06267 0.05856 -0.0399 0.9837 0.1597
-6.250 -0.4201 0.05880 0.05464 -0.0437 0.9733 0.1760
-6.000 -0.3960 0.05547 0.05107 -0.0487 0.9610 0.2041
-5.000 -0.2504 0.03306 0.02523 -0.0617 0.9259 0.0840
-4.750 -0.2221 0.02956 0.02161 -0.0623 0.9157 0.0801
-4.500 -0.1826 0.02726 0.01889 -0.0640 0.9094 0.0795
-4.250 -0.1527 0.02569 0.01701 -0.0639 0.8990 0.0798
-4.000 -0.1176 0.02406 0.01512 -0.0646 0.8912 0.0794
-3.750 -0.0850 0.02277 0.01366 -0.0649 0.8823 0.0805
-3.500 -0.0549 0.02193 0.01265 -0.0647 0.8728 0.0839
-3.250 -0.0246 0.02051 0.01138 -0.0648 0.8645 0.0900
-3.000 -0.0015 0.01984 0.01071 -0.0634 0.8533 0.0959
-2.750 0.0221 0.01907 0.00997 -0.0622 0.8441 0.1072
-2.500 0.0444 0.01833 0.00933 -0.0608 0.8345 0.1338
-2.250 0.0464 0.01587 0.00930 -0.0556 0.8251 0.6576
-2.000 0.0805 0.01581 0.00976 -0.0523 0.8186 0.8701
-1.750 0.2026 0.01661 0.01012 -0.0650 0.8147 0.9580
-1.500 0.2777 0.01649 0.00971 -0.0741 0.8053 0.9838
-1.250 0.3343 0.01613 0.00912 -0.0805 0.7962 0.9989
-1.000 0.3520 0.01607 0.00893 -0.0797 0.7865 1.0000
-0.750 0.3657 0.01613 0.00890 -0.0782 0.7761 1.0000
-0.500 0.3816 0.01615 0.00878 -0.0766 0.7676 1.0000
-0.250 0.3965 0.01630 0.00884 -0.0750 0.7574 1.0000
0.000 0.4131 0.01649 0.00894 -0.0734 0.7484 1.0000
0.250 0.4314 0.01665 0.00898 -0.0718 0.7398 1.0000
0.500 0.4488 0.01694 0.00921 -0.0703 0.7300 1.0000
0.750 0.4699 0.01710 0.00924 -0.0690 0.7226 1.0000
1.000 0.4877 0.01746 0.00958 -0.0675 0.7124 1.0000
1.250 0.5095 0.01767 0.00969 -0.0663 0.7050 1.0000
1.500 0.5289 0.01802 0.01001 -0.0650 0.6951 1.0000
1.750 0.5500 0.01834 0.01027 -0.0637 0.6869 1.0000
2.000 0.5716 0.01861 0.01050 -0.0626 0.6782 1.0000
2.250 0.5921 0.01901 0.01088 -0.0614 0.6693 1.0000
2.500 0.6156 0.01923 0.01104 -0.0603 0.6616 1.0000
2.750 0.6354 0.01970 0.01153 -0.0591 0.6521 1.0000
3.000 0.6602 0.01987 0.01165 -0.0582 0.6451 1.0000
3.250 0.6793 0.02040 0.01223 -0.0569 0.6351 1.0000
3.500 0.7054 0.02052 0.01229 -0.0562 0.6287 1.0000
3.750 0.7238 0.02111 0.01296 -0.0549 0.6185 1.0000
4.000 0.7510 0.02117 0.01297 -0.0542 0.6122 1.0000
4.250 0.7699 0.02163 0.01351 -0.0528 0.6011 1.0000
4.500 0.7924 0.02189 0.01380 -0.0517 0.5917 1.0000
4.750 0.8186 0.02186 0.01377 -0.0509 0.5833 1.0000
5.000 0.8388 0.02227 0.01427 -0.0497 0.5728 1.0000
5.250 0.8680 0.02216 0.01411 -0.0492 0.5663 1.0000
5.500 0.8869 0.02262 0.01470 -0.0479 0.5552 1.0000
5.750 0.9099 0.02282 0.01499 -0.0468 0.5453 1.0000
6.000 0.9391 0.02256 0.01469 -0.0463 0.5368 1.0000
6.250 0.9593 0.02286 0.01512 -0.0450 0.5250 1.0000
6.500 0.9821 0.02304 0.01540 -0.0439 0.5142 1.0000
6.750 1.0087 0.02285 0.01523 -0.0431 0.5030 1.0000
7.000 1.0339 0.02253 0.01491 -0.0420 0.4887 1.0000
7.250 1.0567 0.02230 0.01473 -0.0406 0.4725 1.0000
7.500 1.0793 0.02222 0.01471 -0.0393 0.4571 1.0000
7.750 1.1008 0.02225 0.01481 -0.0379 0.4412 1.0000
8.000 1.1211 0.02232 0.01496 -0.0364 0.4241 1.0000
8.250 1.1412 0.02236 0.01507 -0.0348 0.4056 1.0000
8.500 1.1601 0.02243 0.01513 -0.0330 0.3848 1.0000
8.750 1.1737 0.02270 0.01546 -0.0306 0.3596 1.0000
9.000 1.1844 0.02308 0.01588 -0.0279 0.3311 1.0000
9.250 1.1915 0.02364 0.01638 -0.0248 0.2992 1.0000
9.500 1.1934 0.02456 0.01718 -0.0212 0.2636 1.0000
9.750 1.1903 0.02585 0.01826 -0.0172 0.2297 1.0000
10.000 1.1827 0.02737 0.01957 -0.0127 0.2022 1.0000
10.250 1.1756 0.02921 0.02115 -0.0090 0.1801 1.0000
10.500 1.1715 0.03114 0.02298 -0.0061 0.1600 1.0000
10.750 1.1693 0.03312 0.02485 -0.0038 0.1439 1.0000
11.000 1.1691 0.03514 0.02678 -0.0018 0.1302 1.0000
11.250 1.1712 0.03719 0.02879 -0.0002 0.1177 1.0000
11.500 1.1764 0.03922 0.03079 0.0013 0.1069 1.0000
11.750 1.1841 0.04122 0.03274 0.0026 0.0977 1.0000
12.000 1.1997 0.04305 0.03435 0.0037 0.0888 1.0000
12.250 1.2080 0.04515 0.03672 0.0049 0.0834 1.0000
12.500 1.2347 0.04715 0.03854 0.0055 0.0764 1.0000
12.750 1.2374 0.04948 0.04121 0.0067 0.0732 1.0000
13.000 1.2464 0.05186 0.04376 0.0076 0.0698 1.0000
13.250 1.2813 0.05494 0.04674 0.0075 0.0653 1.0000
13.500 1.2725 0.05774 0.04989 0.0089 0.0642 1.0000
13.750 1.2631 0.06092 0.05339 0.0098 0.0630 1.0000
14.000 1.2531 0.06446 0.05723 0.0103 0.0618 1.0000
14.250 1.2423 0.06841 0.06146 0.0104 0.0610 1.0000
14.500 1.2283 0.07281 0.06612 0.0101 0.0605 1.0000
14.750 1.2103 0.07780 0.07138 0.0092 0.0603 1.0000
15.000 1.1878 0.08344 0.07729 0.0076 0.0602 1.0000
15.250 1.1611 0.08997 0.08408 0.0051 0.0606 1.0000
15.500 1.1298 0.09764 0.09199 0.0015 0.0612 1.0000
15.750 1.0954 0.10660 0.10118 -0.0034 0.0620 1.0000
16.000 1.0583 0.11720 0.11195 -0.0096 0.0632 1.0000
16.250 1.0251 0.12839 0.12324 -0.0161 0.0645 1.0000
16.500 0.9959 0.13993 0.13481 -0.0226 0.0653 1.0000
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Polar data table (+)
Polar graphs
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