BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Reynolds number: 200,000 Max Cl/Cd: 49.73 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v13009-il-200000.txt Download as CSV file: xf-v13009-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5872 0.08558 0.08204 -0.0035 1.0000 0.0599
-8.250 -0.5923 0.08028 0.07677 -0.0088 1.0000 0.0610
-8.000 -0.5970 0.07470 0.07115 -0.0140 1.0000 0.0624
-7.750 -0.6143 0.06826 0.06417 -0.0221 1.0000 0.0662
-7.500 -0.6168 0.06273 0.05834 -0.0230 1.0000 0.0669
-7.250 -0.6034 0.05740 0.05319 -0.0230 1.0000 0.0681
-7.000 -0.5892 0.05448 0.05030 -0.0225 1.0000 0.0692
-6.750 -0.5755 0.05172 0.04748 -0.0221 1.0000 0.0708
-6.500 -0.5617 0.04889 0.04453 -0.0218 1.0000 0.0736
-6.250 -0.5545 0.04504 0.04000 -0.0210 1.0000 0.0809
-6.000 -0.5372 0.04202 0.03711 -0.0205 1.0000 0.0827
-5.750 -0.5269 0.03160 0.02555 -0.0173 1.0000 0.0525
-5.500 -0.5109 0.02736 0.02082 -0.0153 1.0000 0.0493
-5.250 -0.4919 0.02412 0.01704 -0.0134 1.0000 0.0482
-5.000 -0.4702 0.02246 0.01517 -0.0121 1.0000 0.0490
-4.750 -0.4479 0.02134 0.01390 -0.0110 1.0000 0.0511
-4.500 -0.4251 0.02008 0.01241 -0.0097 1.0000 0.0530
-4.250 -0.4019 0.01895 0.01106 -0.0085 1.0000 0.0545
-4.000 -0.3790 0.01733 0.00935 -0.0074 1.0000 0.0569
-3.750 -0.3564 0.01654 0.00860 -0.0064 1.0000 0.0603
-3.500 -0.3337 0.01607 0.00806 -0.0053 1.0000 0.0654
-3.250 -0.3115 0.01502 0.00707 -0.0043 1.0000 0.0710
-3.000 -0.2892 0.01454 0.00657 -0.0032 1.0000 0.0779
-2.750 -0.2675 0.01384 0.00596 -0.0022 1.0000 0.0864
-2.500 -0.2454 0.01340 0.00553 -0.0013 1.0000 0.0957
-2.250 -0.2234 0.01305 0.00525 -0.0005 1.0000 0.1063
-2.000 -0.1918 0.01260 0.00489 -0.0017 0.9972 0.1205
-1.750 -0.1473 0.01202 0.00449 -0.0053 0.9894 0.1459
-1.500 -0.1101 0.00974 0.00403 -0.0084 0.9823 0.5458
-1.250 -0.0787 0.00884 0.00425 -0.0074 0.9718 0.8352
-1.000 -0.0321 0.00883 0.00437 -0.0094 0.9622 0.9262
-0.750 0.0285 0.00891 0.00436 -0.0149 0.9553 0.9651
-0.500 0.0912 0.00890 0.00426 -0.0213 0.9430 0.9846
-0.250 0.1589 0.00877 0.00403 -0.0289 0.9252 1.0000
0.000 0.1871 0.00863 0.00379 -0.0287 0.8922 1.0000
0.250 0.2110 0.00855 0.00359 -0.0275 0.8605 1.0000
0.500 0.2342 0.00854 0.00343 -0.0262 0.8300 1.0000
0.750 0.2572 0.00856 0.00331 -0.0250 0.7988 1.0000
1.000 0.2805 0.00862 0.00321 -0.0237 0.7666 1.0000
1.250 0.3040 0.00871 0.00314 -0.0226 0.7331 1.0000
1.500 0.3277 0.00881 0.00309 -0.0215 0.6988 1.0000
1.750 0.3515 0.00895 0.00307 -0.0205 0.6631 1.0000
2.000 0.3751 0.00913 0.00306 -0.0194 0.6259 1.0000
2.250 0.3988 0.00933 0.00308 -0.0184 0.5859 1.0000
2.500 0.4222 0.00958 0.00313 -0.0174 0.5441 1.0000
2.750 0.4454 0.00988 0.00320 -0.0164 0.4995 1.0000
3.000 0.4685 0.01021 0.00331 -0.0154 0.4519 1.0000
3.250 0.4913 0.01060 0.00345 -0.0144 0.4008 1.0000
3.500 0.5137 0.01107 0.00365 -0.0134 0.3533 1.0000
3.750 0.5365 0.01154 0.00389 -0.0125 0.3162 1.0000
4.000 0.5600 0.01197 0.00416 -0.0117 0.2895 1.0000
4.250 0.5837 0.01239 0.00446 -0.0109 0.2704 1.0000
4.500 0.6078 0.01279 0.00476 -0.0102 0.2552 1.0000
4.750 0.6322 0.01317 0.00509 -0.0096 0.2426 1.0000
5.000 0.6566 0.01356 0.00543 -0.0089 0.2312 1.0000
5.250 0.6808 0.01400 0.00579 -0.0083 0.2208 1.0000
5.500 0.7056 0.01433 0.00614 -0.0077 0.2103 1.0000
5.750 0.7301 0.01474 0.00654 -0.0071 0.1998 1.0000
6.000 0.7542 0.01523 0.00699 -0.0065 0.1894 1.0000
6.250 0.7783 0.01570 0.00742 -0.0059 0.1785 1.0000
6.500 0.8026 0.01614 0.00790 -0.0053 0.1671 1.0000
6.750 0.8264 0.01670 0.00846 -0.0047 0.1563 1.0000
7.000 0.8498 0.01733 0.00904 -0.0041 0.1462 1.0000
7.250 0.8742 0.01769 0.00948 -0.0035 0.1362 1.0000
7.500 0.8979 0.01822 0.01006 -0.0029 0.1269 1.0000
7.750 0.9211 0.01882 0.01059 -0.0022 0.1188 1.0000
8.000 0.9453 0.01925 0.01117 -0.0016 0.1110 1.0000
8.250 0.9679 0.02001 0.01189 -0.0009 0.1046 1.0000
8.500 0.9912 0.02058 0.01256 -0.0002 0.0981 1.0000
8.750 1.0128 0.02158 0.01352 0.0005 0.0927 1.0000
9.000 1.0355 0.02238 0.01447 0.0013 0.0881 1.0000
9.250 1.0574 0.02326 0.01537 0.0020 0.0841 1.0000
9.500 1.0783 0.02476 0.01690 0.0027 0.0805 1.0000
9.750 1.0995 0.02570 0.01806 0.0036 0.0772 1.0000
10.000 1.1204 0.02673 0.01920 0.0044 0.0741 1.0000
10.250 1.1411 0.02799 0.02047 0.0051 0.0715 1.0000
10.500 1.1590 0.03002 0.02266 0.0060 0.0690 1.0000
10.750 1.1767 0.03115 0.02409 0.0071 0.0665 1.0000
11.000 1.1941 0.03222 0.02533 0.0081 0.0637 1.0000
11.250 1.2127 0.03309 0.02616 0.0088 0.0609 1.0000
11.500 1.2253 0.03531 0.02855 0.0100 0.0584 1.0000
11.750 1.2367 0.03654 0.03009 0.0115 0.0561 1.0000
12.000 1.2485 0.03773 0.03147 0.0128 0.0536 1.0000
12.250 1.2629 0.03866 0.03239 0.0138 0.0514 1.0000
12.500 1.2689 0.04134 0.03516 0.0151 0.0493 1.0000
12.750 1.2664 0.04303 0.03720 0.0175 0.0479 1.0000
13.000 1.2614 0.04506 0.03947 0.0197 0.0464 1.0000
13.250 1.2569 0.04725 0.04185 0.0210 0.0449 1.0000
13.500 1.2570 0.04922 0.04390 0.0216 0.0435 1.0000
13.750 1.2627 0.05112 0.04574 0.0220 0.0419 1.0000
14.000 1.2458 0.05584 0.05068 0.0215 0.0411 1.0000
14.250 1.2262 0.06087 0.05599 0.0192 0.0407 1.0000
14.500 1.2034 0.06717 0.06255 0.0156 0.0405 1.0000
14.750 1.1770 0.07482 0.07045 0.0106 0.0405 1.0000
15.000 1.1463 0.08393 0.07977 0.0045 0.0407 1.0000
15.250 1.1110 0.09452 0.09054 -0.0024 0.0411 1.0000
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Polar data table (+)
Polar graphs
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