BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.68 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr7b-il-1000000-n5.txt Download as CSV file: xf-vr7b-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6549 0.18185 0.18020 0.0616 0.9053 0.0047
-14.000 -0.6492 0.17769 0.17604 0.0597 0.9022 0.0047
-10.500 -0.9670 0.02796 0.02437 -0.0154 0.8323 0.0080
-10.250 -0.9486 0.02588 0.02198 -0.0151 0.8210 0.0081
-10.000 -0.9294 0.02384 0.01965 -0.0148 0.8094 0.0083
-9.750 -0.9062 0.02273 0.01837 -0.0146 0.7970 0.0084
-9.500 -0.8813 0.02196 0.01746 -0.0145 0.7834 0.0085
-9.250 -0.8558 0.02129 0.01666 -0.0145 0.7692 0.0087
-9.000 -0.8298 0.02065 0.01589 -0.0145 0.7546 0.0088
-8.750 -0.8033 0.02007 0.01520 -0.0145 0.7393 0.0090
-8.250 -0.7498 0.01889 0.01374 -0.0146 0.7121 0.0094
-8.000 -0.7229 0.01817 0.01286 -0.0147 0.7018 0.0097
-7.500 -0.6687 0.01659 0.01096 -0.0149 0.6849 0.0102
-7.250 -0.6411 0.01594 0.01016 -0.0150 0.6779 0.0104
-7.000 -0.6132 0.01539 0.00949 -0.0151 0.6724 0.0106
-6.750 -0.5850 0.01490 0.00890 -0.0153 0.6668 0.0107
-6.500 -0.5575 0.01402 0.00790 -0.0154 0.6613 0.0110
-6.250 -0.5291 0.01357 0.00738 -0.0156 0.6561 0.0113
-6.000 -0.5004 0.01325 0.00702 -0.0159 0.6501 0.0116
-5.500 -0.4428 0.01257 0.00623 -0.0163 0.6390 0.0122
-5.250 -0.4138 0.01218 0.00578 -0.0166 0.6340 0.0124
-5.000 -0.3848 0.01183 0.00536 -0.0168 0.6292 0.0127
-4.750 -0.3556 0.01148 0.00496 -0.0171 0.6247 0.0130
-4.500 -0.3263 0.01116 0.00459 -0.0174 0.6194 0.0132
-4.250 -0.2969 0.01089 0.00426 -0.0177 0.6140 0.0135
-4.000 -0.2674 0.01066 0.00397 -0.0180 0.6096 0.0137
-3.750 -0.2379 0.01029 0.00358 -0.0184 0.6052 0.0143
-3.500 -0.2083 0.01005 0.00332 -0.0187 0.6006 0.0148
-3.250 -0.1786 0.00987 0.00310 -0.0191 0.5958 0.0153
-3.000 -0.1488 0.00968 0.00289 -0.0194 0.5910 0.0158
-2.750 -0.1190 0.00951 0.00269 -0.0198 0.5854 0.0164
-2.500 -0.0891 0.00937 0.00251 -0.0202 0.5801 0.0169
-2.250 -0.0592 0.00922 0.00234 -0.0206 0.5752 0.0176
-2.000 -0.0292 0.00906 0.00217 -0.0210 0.5690 0.0189
-1.750 0.0008 0.00896 0.00204 -0.0214 0.5628 0.0205
-1.500 0.0307 0.00885 0.00193 -0.0218 0.5567 0.0230
-1.250 0.0608 0.00876 0.00183 -0.0222 0.5498 0.0281
-1.000 0.0908 0.00865 0.00175 -0.0227 0.5437 0.0385
-0.750 0.1209 0.00853 0.00167 -0.0232 0.5367 0.0569
-0.500 0.1510 0.00844 0.00160 -0.0237 0.5305 0.0791
-0.250 0.1813 0.00802 0.00152 -0.0244 0.5243 0.1940
0.000 0.2119 0.00736 0.00143 -0.0256 0.5172 0.3878
0.250 0.2422 0.00687 0.00144 -0.0264 0.5106 0.5517
0.500 0.2724 0.00675 0.00145 -0.0270 0.5032 0.6068
0.750 0.3024 0.00669 0.00145 -0.0275 0.4952 0.6381
1.000 0.3325 0.00659 0.00147 -0.0280 0.4855 0.6896
1.250 0.3621 0.00647 0.00154 -0.0284 0.4771 0.7632
1.500 0.3918 0.00648 0.00157 -0.0288 0.4684 0.7851
1.750 0.4215 0.00650 0.00160 -0.0292 0.4591 0.7998
2.000 0.4510 0.00653 0.00165 -0.0296 0.4499 0.8182
2.250 0.4802 0.00657 0.00172 -0.0298 0.4389 0.8422
2.500 0.5086 0.00658 0.00179 -0.0299 0.4295 0.8695
2.750 0.5368 0.00665 0.00186 -0.0299 0.4180 0.8903
3.000 0.5651 0.00676 0.00195 -0.0300 0.4045 0.9075
3.250 0.5941 0.00690 0.00203 -0.0304 0.3925 0.9205
3.500 0.6232 0.00700 0.00211 -0.0307 0.3828 0.9308
3.750 0.6512 0.00709 0.00219 -0.0308 0.3747 0.9405
4.000 0.6789 0.00716 0.00226 -0.0307 0.3666 0.9507
4.500 0.7357 0.00732 0.00241 -0.0311 0.3496 0.9723
4.750 0.7667 0.00741 0.00250 -0.0319 0.3416 1.0000
5.000 0.7967 0.00760 0.00263 -0.0326 0.3295 1.0000
5.250 0.8265 0.00785 0.00280 -0.0333 0.3083 1.0000
5.500 0.8561 0.00812 0.00299 -0.0340 0.2886 1.0000
5.750 0.8856 0.00838 0.00318 -0.0346 0.2728 1.0000
6.000 0.9149 0.00872 0.00342 -0.0353 0.2498 1.0000
6.250 0.9439 0.00914 0.00371 -0.0360 0.2226 1.0000
6.500 0.9721 0.00980 0.00414 -0.0369 0.1821 1.0000
6.750 1.0004 0.01028 0.00451 -0.0375 0.1560 1.0000
7.000 1.0282 0.01081 0.00489 -0.0381 0.1305 1.0000
7.250 1.0560 0.01126 0.00525 -0.0387 0.1128 1.0000
7.500 1.0832 0.01180 0.00568 -0.0392 0.0909 1.0000
7.750 1.1103 0.01229 0.00609 -0.0397 0.0765 1.0000
8.000 1.1374 0.01272 0.00648 -0.0401 0.0673 1.0000
8.250 1.1642 0.01315 0.00689 -0.0404 0.0599 1.0000
8.500 1.1908 0.01357 0.00729 -0.0408 0.0550 1.0000
8.750 1.2172 0.01398 0.00770 -0.0410 0.0507 1.0000
9.000 1.2437 0.01434 0.00808 -0.0413 0.0470 1.0000
9.250 1.2689 0.01486 0.00858 -0.0415 0.0405 1.0000
9.750 1.3176 0.01598 0.00964 -0.0418 0.0293 1.0000
10.000 1.3412 0.01655 0.01021 -0.0418 0.0257 1.0000
10.250 1.3640 0.01717 0.01084 -0.0417 0.0228 1.0000
10.500 1.3866 0.01776 0.01145 -0.0417 0.0209 1.0000
10.750 1.4082 0.01840 0.01212 -0.0415 0.0193 1.0000
11.000 1.4283 0.01914 0.01287 -0.0412 0.0178 1.0000
11.250 1.4482 0.01985 0.01363 -0.0410 0.0170 1.0000
11.500 1.4666 0.02062 0.01445 -0.0407 0.0163 1.0000
11.750 1.4804 0.02150 0.01539 -0.0397 0.0156 1.0000
12.000 1.4921 0.02253 0.01646 -0.0387 0.0149 1.0000
12.250 1.5034 0.02370 0.01767 -0.0377 0.0143 1.0000
12.500 1.5136 0.02504 0.01907 -0.0369 0.0137 1.0000
12.750 1.5259 0.02626 0.02037 -0.0364 0.0134 1.0000
13.000 1.5371 0.02763 0.02180 -0.0359 0.0130 1.0000
13.250 1.5473 0.02913 0.02337 -0.0355 0.0125 1.0000
13.500 1.5563 0.03080 0.02510 -0.0352 0.0121 1.0000
13.750 1.5639 0.03265 0.02701 -0.0350 0.0116 1.0000
14.000 1.5701 0.03469 0.02911 -0.0348 0.0112 1.0000
14.250 1.5744 0.03698 0.03147 -0.0346 0.0108 1.0000
14.500 1.5789 0.03926 0.03384 -0.0346 0.0106 1.0000
14.750 1.5839 0.04150 0.03616 -0.0345 0.0103 1.0000
15.000 1.5876 0.04391 0.03865 -0.0345 0.0100 1.0000
15.250 1.5899 0.04646 0.04129 -0.0346 0.0098 1.0000
15.500 1.5911 0.04918 0.04409 -0.0347 0.0094 1.0000
15.750 1.5913 0.05209 0.04707 -0.0349 0.0091 1.0000
16.000 1.5903 0.05519 0.05024 -0.0352 0.0088 1.0000
16.250 1.5882 0.05851 0.05363 -0.0357 0.0085 1.0000
16.500 1.5848 0.06210 0.05731 -0.0363 0.0082 1.0000
16.750 1.5826 0.06557 0.06088 -0.0370 0.0080 1.0000
17.000 1.5797 0.06922 0.06461 -0.0377 0.0078 1.0000
17.250 1.5758 0.07309 0.06858 -0.0386 0.0075 1.0000
17.500 1.5709 0.07714 0.07273 -0.0397 0.0073 1.0000
17.750 1.5649 0.08138 0.07706 -0.0408 0.0071 1.0000
18.000 1.5581 0.08582 0.08159 -0.0420 0.0069 1.0000
18.250 1.5505 0.09046 0.08632 -0.0435 0.0067 1.0000
18.500 1.5419 0.09529 0.09124 -0.0450 0.0066 1.0000
18.750 1.5323 0.10032 0.09637 -0.0467 0.0064 1.0000
19.000 1.5216 0.10562 0.10175 -0.0486 0.0062 1.0000
19.250 1.5103 0.11110 0.10734 -0.0506 0.0061 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BOEING-VERTOL VR-7 AIRFOIL WITH TAB (vr7b-il)