HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL (tempest1-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL (tempest1-il) Reynolds number: 50,000 Max Cl/Cd: 30.91 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tempest1-il-50000.txt Download as CSV file: xf-tempest1-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5155 0.10104 0.09367 -0.0428 1.0000 0.1715
-10.750 -0.5561 0.09014 0.08292 -0.0493 1.0000 0.1553
-10.500 -0.7061 0.07656 0.06936 -0.0534 1.0000 0.1312
-10.250 -0.7265 0.07323 0.06603 -0.0497 1.0000 0.1305
-10.000 -0.7484 0.07010 0.06286 -0.0454 1.0000 0.1297
-9.750 -0.7712 0.06691 0.05959 -0.0408 1.0000 0.1290
-9.500 -0.7922 0.06385 0.05639 -0.0359 1.0000 0.1282
-9.250 -0.8127 0.06083 0.05317 -0.0307 1.0000 0.1280
-9.000 -0.8299 0.05788 0.04997 -0.0254 1.0000 0.1280
-8.750 -0.8454 0.05506 0.04682 -0.0200 1.0000 0.1290
-8.500 -0.8573 0.05235 0.04371 -0.0148 1.0000 0.1303
-8.250 -0.8566 0.04962 0.04084 -0.0112 1.0000 0.1344
-8.000 -0.8513 0.04739 0.03849 -0.0080 1.0000 0.1396
-7.750 -0.8538 0.04489 0.03552 -0.0034 1.0000 0.1440
-7.500 -0.8462 0.04261 0.03311 -0.0005 1.0000 0.1512
-7.250 -0.8414 0.04058 0.03068 0.0033 1.0000 0.1599
-7.000 -0.8289 0.03860 0.02865 0.0058 1.0000 0.1722
-6.750 -0.8169 0.03673 0.02667 0.0084 1.0000 0.1863
-6.500 -0.8055 0.03508 0.02487 0.0111 1.0000 0.2041
-6.250 -0.7913 0.03348 0.02328 0.0135 1.0000 0.2248
-6.000 -0.7765 0.03213 0.02198 0.0157 1.0000 0.2488
-5.750 -0.7607 0.03083 0.02077 0.0177 1.0000 0.2748
-5.500 -0.7444 0.02963 0.01966 0.0197 1.0000 0.3039
-5.250 -0.7277 0.02851 0.01873 0.0217 1.0000 0.3379
-5.000 -0.7109 0.02740 0.01787 0.0238 1.0000 0.3795
-4.750 -0.6956 0.02632 0.01725 0.0262 1.0000 0.4359
-4.500 -0.6844 0.02536 0.01700 0.0301 1.0000 0.5231
-4.250 -0.6703 0.02514 0.01753 0.0352 1.0000 0.6464
-4.000 -0.6376 0.02668 0.01926 0.0388 1.0000 0.7465
-3.750 -0.5769 0.02947 0.02175 0.0378 1.0000 0.8110
-3.500 -0.4597 0.03323 0.02488 0.0269 1.0000 0.8581
-3.250 -0.3444 0.03546 0.02653 0.0139 1.0000 0.8983
-3.000 -0.2445 0.03631 0.02696 0.0013 1.0000 0.9385
-2.750 -0.1440 0.03596 0.02623 -0.0134 1.0000 0.9727
-2.500 -0.0543 0.03500 0.02495 -0.0275 1.0000 1.0000
-2.250 -0.0587 0.03470 0.02463 -0.0247 1.0000 1.0000
-2.000 -0.0633 0.03445 0.02433 -0.0218 1.0000 1.0000
-1.750 -0.0680 0.03422 0.02407 -0.0188 1.0000 1.0000
-1.500 -0.0727 0.03403 0.02383 -0.0158 1.0000 1.0000
-1.250 -0.0773 0.03387 0.02363 -0.0128 1.0000 1.0000
-1.000 -0.0815 0.03374 0.02345 -0.0097 1.0000 1.0000
-0.750 -0.0853 0.03365 0.02331 -0.0067 1.0000 1.0000
-0.500 -0.0884 0.03360 0.02319 -0.0037 1.0000 1.0000
-0.250 -0.0907 0.03358 0.02312 -0.0007 1.0000 1.0000
0.000 -0.0919 0.03362 0.02310 0.0023 1.0000 1.0000
0.250 -0.0922 0.03371 0.02312 0.0051 1.0000 1.0000
0.500 -0.0914 0.03384 0.02320 0.0078 1.0000 1.0000
0.750 -0.0894 0.03404 0.02333 0.0104 1.0000 1.0000
1.000 -0.0530 0.03487 0.02411 0.0064 0.9902 1.0000
1.250 -0.0132 0.03579 0.02500 0.0020 0.9773 1.0000
1.500 0.0222 0.03664 0.02583 -0.0015 0.9644 1.0000
1.750 0.0563 0.03748 0.02665 -0.0045 0.9511 1.0000
2.000 0.0899 0.03832 0.02748 -0.0073 0.9378 1.0000
2.250 0.1248 0.03919 0.02836 -0.0102 0.9246 1.0000
2.500 0.1523 0.03988 0.02906 -0.0116 0.9106 1.0000
2.750 0.1788 0.04056 0.02977 -0.0127 0.8961 1.0000
3.000 0.2057 0.04126 0.03051 -0.0138 0.8813 1.0000
3.250 0.2329 0.04196 0.03125 -0.0148 0.8662 1.0000
3.500 0.2607 0.04266 0.03200 -0.0158 0.8508 1.0000
3.750 0.2911 0.04332 0.03274 -0.0170 0.8347 1.0000
4.000 0.3216 0.04394 0.03344 -0.0181 0.8186 1.0000
4.250 0.3559 0.04450 0.03410 -0.0195 0.8020 1.0000
4.500 0.3796 0.04506 0.03475 -0.0193 0.7848 1.0000
4.750 0.3981 0.04565 0.03542 -0.0182 0.7666 1.0000
5.000 0.4224 0.04614 0.03602 -0.0178 0.7480 1.0000
5.250 0.4540 0.04644 0.03645 -0.0182 0.7294 1.0000
5.500 0.5001 0.04618 0.03641 -0.0199 0.7105 1.0000
5.750 0.5300 0.04616 0.03655 -0.0193 0.6902 1.0000
6.000 0.5584 0.04597 0.03652 -0.0183 0.6686 1.0000
6.250 0.6745 0.04150 0.03260 -0.0256 0.6476 1.0000
6.500 0.7045 0.04057 0.03187 -0.0237 0.6230 1.0000
6.750 0.8584 0.03332 0.02522 -0.0349 0.5838 1.0000
7.000 0.8873 0.03223 0.02421 -0.0325 0.5473 1.0000
7.250 0.9223 0.03092 0.02286 -0.0306 0.5030 1.0000
7.500 0.9418 0.03047 0.02222 -0.0271 0.4587 1.0000
8.000 0.9566 0.03131 0.02258 -0.0180 0.3764 1.0000
8.250 0.9655 0.03216 0.02308 -0.0141 0.3368 1.0000
8.500 0.9680 0.03333 0.02405 -0.0095 0.3031 1.0000
8.750 0.9725 0.03465 0.02516 -0.0054 0.2714 1.0000
9.000 0.9787 0.03617 0.02647 -0.0018 0.2419 1.0000
9.250 0.9888 0.03784 0.02790 0.0011 0.2148 1.0000
9.500 0.9936 0.03961 0.02969 0.0048 0.1939 1.0000
9.750 1.0137 0.04177 0.03158 0.0059 0.1722 1.0000
10.000 1.0265 0.04407 0.03392 0.0081 0.1576 1.0000
10.250 1.0250 0.04609 0.03628 0.0124 0.1486 1.0000
10.500 1.0331 0.04868 0.03899 0.0150 0.1401 1.0000
10.750 1.0397 0.05106 0.04153 0.0178 0.1326 1.0000
11.000 1.0401 0.05389 0.04452 0.0211 0.1275 1.0000
11.250 1.0248 0.05644 0.04743 0.0263 0.1251 1.0000
11.500 1.0087 0.05899 0.05023 0.0314 0.1235 1.0000
11.750 0.9899 0.06176 0.05323 0.0362 0.1224 1.0000
12.000 0.9675 0.06487 0.05656 0.0405 0.1219 1.0000
12.250 0.9396 0.06845 0.06035 0.0441 0.1221 1.0000
12.500 0.9063 0.07278 0.06488 0.0466 0.1233 1.0000
12.750 0.8703 0.07803 0.07030 0.0476 0.1249 1.0000
13.000 0.8350 0.08422 0.07659 0.0470 0.1265 1.0000
13.250 0.8025 0.09131 0.08375 0.0451 0.1282 1.0000
13.500 0.7783 0.09869 0.09114 0.0427 0.1294 1.0000
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Polar data table (+)
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