BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Reynolds number: 200,000 Max Cl/Cd: 72.92 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr7b-il-200000.txt Download as CSV file: xf-vr7b-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-7 AIRFOIL WITH TAB
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4953 0.08791 0.08505 -0.0205 1.0000 0.0478
-8.500 -0.5054 0.08040 0.07737 -0.0333 1.0000 0.0480
-8.250 -0.5054 0.07555 0.07221 -0.0395 0.9710 0.0482
-8.000 -0.4945 0.07000 0.06694 -0.0369 0.9577 0.0496
-7.750 -0.4918 0.06810 0.06504 -0.0346 0.9399 0.0504
-7.500 -0.4899 0.06569 0.06257 -0.0335 0.9240 0.0514
-7.250 -0.4858 0.06257 0.05935 -0.0335 0.9102 0.0530
-7.000 -0.4789 0.05880 0.05539 -0.0347 0.8974 0.0559
-6.750 -0.4763 0.05319 0.04909 -0.0372 0.8856 0.0606
-6.500 -0.4625 0.05034 0.04636 -0.0361 0.8764 0.0623
-6.250 -0.4480 0.04798 0.04394 -0.0352 0.8669 0.0650
-5.750 -0.4166 0.04144 0.03668 -0.0348 0.8502 0.0752
-5.500 -0.3953 0.03914 0.03433 -0.0347 0.8410 0.0788
-5.250 -0.3768 0.03660 0.03133 -0.0340 0.8343 0.0887
-5.000 -0.3531 0.03453 0.02923 -0.0340 0.8251 0.0940
-4.750 -0.3328 0.03249 0.02696 -0.0333 0.8185 0.1058
-4.500 -0.3081 0.03081 0.02516 -0.0337 0.8096 0.1211
-4.250 -0.2652 0.02418 0.01662 -0.0300 0.8045 0.0488
-4.000 -0.2372 0.02235 0.01463 -0.0297 0.7967 0.0474
-3.750 -0.2107 0.02071 0.01276 -0.0289 0.7892 0.0470
-3.500 -0.1826 0.01955 0.01142 -0.0285 0.7806 0.0474
-3.250 -0.1561 0.01835 0.01006 -0.0278 0.7729 0.0492
-3.000 -0.1284 0.01717 0.00890 -0.0277 0.7645 0.0510
-2.750 -0.1014 0.01636 0.00805 -0.0272 0.7575 0.0528
-2.500 -0.0729 0.01569 0.00736 -0.0272 0.7500 0.0557
-2.250 -0.0448 0.01517 0.00677 -0.0271 0.7430 0.0599
-2.000 -0.0164 0.01445 0.00606 -0.0273 0.7361 0.0683
-1.750 0.0127 0.01383 0.00539 -0.0275 0.7286 0.0850
-1.500 0.0338 0.01106 0.00508 -0.0271 0.7228 0.6701
-1.250 0.0532 0.01076 0.00522 -0.0242 0.7153 0.8056
-1.000 0.0689 0.01072 0.00525 -0.0203 0.7096 0.8749
-0.750 0.0867 0.01072 0.00527 -0.0170 0.7021 0.9329
-0.500 0.1296 0.01064 0.00506 -0.0187 0.6952 0.9824
-0.250 0.1873 0.01073 0.00499 -0.0247 0.6871 1.0000
0.000 0.2101 0.01070 0.00482 -0.0242 0.6801 1.0000
0.250 0.2343 0.01075 0.00475 -0.0240 0.6728 1.0000
0.500 0.2599 0.01081 0.00469 -0.0238 0.6655 1.0000
0.750 0.2869 0.01091 0.00468 -0.0239 0.6587 1.0000
1.000 0.3155 0.01101 0.00469 -0.0243 0.6508 1.0000
1.250 0.3436 0.01114 0.00469 -0.0244 0.6445 1.0000
1.500 0.3734 0.01124 0.00476 -0.0250 0.6361 1.0000
1.750 0.4016 0.01137 0.00476 -0.0251 0.6300 1.0000
2.000 0.4319 0.01149 0.00489 -0.0258 0.6213 1.0000
2.250 0.4606 0.01161 0.00489 -0.0260 0.6149 1.0000
2.500 0.4907 0.01174 0.00504 -0.0267 0.6064 1.0000
2.750 0.5196 0.01185 0.00507 -0.0269 0.5996 1.0000
3.000 0.5495 0.01199 0.00522 -0.0275 0.5911 1.0000
3.250 0.5784 0.01210 0.00526 -0.0277 0.5841 1.0000
3.500 0.6083 0.01222 0.00540 -0.0283 0.5748 1.0000
3.750 0.6369 0.01230 0.00539 -0.0283 0.5674 1.0000
4.000 0.6667 0.01241 0.00557 -0.0289 0.5573 1.0000
4.250 0.6958 0.01253 0.00566 -0.0292 0.5494 1.0000
4.500 0.7251 0.01265 0.00579 -0.0296 0.5403 1.0000
4.750 0.7543 0.01280 0.00594 -0.0300 0.5312 1.0000
5.000 0.7830 0.01290 0.00601 -0.0302 0.5222 1.0000
5.250 0.8123 0.01306 0.00623 -0.0307 0.5117 1.0000
5.500 0.8411 0.01324 0.00641 -0.0310 0.5031 1.0000
5.750 0.8699 0.01338 0.00658 -0.0314 0.4929 1.0000
6.000 0.8987 0.01352 0.00677 -0.0317 0.4808 1.0000
6.250 0.9272 0.01366 0.00693 -0.0321 0.4679 1.0000
6.500 0.9555 0.01382 0.00712 -0.0323 0.4547 1.0000
6.750 0.9837 0.01402 0.00734 -0.0326 0.4423 1.0000
7.000 1.0118 0.01423 0.00758 -0.0329 0.4293 1.0000
7.250 1.0396 0.01445 0.00786 -0.0332 0.4148 1.0000
7.500 1.0672 0.01471 0.00817 -0.0335 0.3990 1.0000
7.750 1.0944 0.01501 0.00853 -0.0338 0.3810 1.0000
8.000 1.1208 0.01537 0.00891 -0.0341 0.3586 1.0000
8.250 1.1465 0.01579 0.00935 -0.0344 0.3308 1.0000
8.500 1.1709 0.01637 0.00986 -0.0346 0.2970 1.0000
8.750 1.1932 0.01720 0.01056 -0.0347 0.2563 1.0000
9.000 1.2124 0.01837 0.01153 -0.0346 0.2111 1.0000
9.250 1.2280 0.01984 0.01277 -0.0342 0.1719 1.0000
9.500 1.2415 0.02141 0.01415 -0.0337 0.1373 1.0000
9.750 1.2532 0.02300 0.01562 -0.0329 0.1132 1.0000
10.000 1.2615 0.02475 0.01727 -0.0319 0.0969 1.0000
10.250 1.2652 0.02652 0.01901 -0.0304 0.0856 1.0000
10.500 1.2692 0.02839 0.02092 -0.0290 0.0762 1.0000
10.750 1.2701 0.03066 0.02320 -0.0278 0.0693 1.0000
11.000 1.2733 0.03283 0.02541 -0.0269 0.0635 1.0000
11.250 1.2737 0.03534 0.02793 -0.0258 0.0592 1.0000
11.500 1.2800 0.03736 0.03005 -0.0252 0.0552 1.0000
11.750 1.2833 0.03967 0.03236 -0.0246 0.0520 1.0000
12.000 1.2873 0.04194 0.03466 -0.0234 0.0492 1.0000
12.250 1.2948 0.04393 0.03681 -0.0229 0.0469 1.0000
12.500 1.3016 0.04598 0.03893 -0.0223 0.0448 1.0000
12.750 1.3078 0.04808 0.04104 -0.0217 0.0429 1.0000
13.000 1.3162 0.05007 0.04301 -0.0201 0.0408 1.0000
13.250 1.3220 0.05232 0.04546 -0.0198 0.0395 1.0000
13.500 1.3279 0.05460 0.04790 -0.0193 0.0381 1.0000
13.750 1.3336 0.05695 0.05037 -0.0189 0.0369 1.0000
14.000 1.3383 0.05937 0.05290 -0.0186 0.0357 1.0000
14.250 1.3439 0.06169 0.05526 -0.0182 0.0345 1.0000
14.500 1.3508 0.06444 0.05807 -0.0168 0.0331 1.0000
14.750 1.3470 0.06788 0.06176 -0.0173 0.0326 1.0000
15.000 1.3425 0.07154 0.06566 -0.0177 0.0320 1.0000
15.250 1.3369 0.07552 0.06986 -0.0183 0.0314 1.0000
15.500 1.3296 0.07985 0.07442 -0.0191 0.0310 1.0000
15.750 1.3202 0.08458 0.07937 -0.0203 0.0306 1.0000
16.000 1.3091 0.08974 0.08474 -0.0220 0.0302 1.0000
16.250 1.2960 0.09537 0.09059 -0.0241 0.0300 1.0000
16.500 1.2807 0.10156 0.09700 -0.0268 0.0298 1.0000
16.750 1.2625 0.10857 0.10423 -0.0302 0.0297 1.0000
17.000 1.2399 0.11684 0.11274 -0.0347 0.0297 1.0000
17.250 1.2106 0.12703 0.12319 -0.0408 0.0300 1.0000
17.500 1.1735 0.13985 0.13627 -0.0490 0.0307 1.0000
17.750 1.1303 0.15567 0.15232 -0.0594 0.0317 1.0000
18.000 1.0820 0.17513 0.17188 -0.0717 0.0329 1.0000
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Polar data table (+)
Polar graphs
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