RAE 5215 AIRFOIL (rae5215-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 5215 AIRFOIL (rae5215-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.05 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5215-il-1000000-n5.txt Download as CSV file: xf-rae5215-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE 5215 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-15.000 -1.1147 0.06345 0.06084 -0.0312 1.0000 0.0065
-14.750 -1.1542 0.05238 0.04951 -0.0396 1.0000 0.0064
-14.500 -1.1739 0.04585 0.04278 -0.0441 1.0000 0.0064
-14.250 -1.1853 0.04097 0.03773 -0.0471 1.0000 0.0064
-14.000 -1.1914 0.03706 0.03365 -0.0493 1.0000 0.0064
-13.750 -1.1941 0.03383 0.03026 -0.0510 1.0000 0.0064
-13.500 -1.1928 0.03131 0.02758 -0.0519 1.0000 0.0065
-13.250 -1.1828 0.02939 0.02550 -0.0520 1.0000 0.0065
-13.000 -1.1695 0.02773 0.02370 -0.0520 1.0000 0.0065
-12.750 -1.1536 0.02626 0.02209 -0.0519 1.0000 0.0066
-12.500 -1.1359 0.02493 0.02064 -0.0518 1.0000 0.0066
-12.250 -1.1167 0.02372 0.01931 -0.0517 1.0000 0.0067
-12.000 -1.0963 0.02261 0.01808 -0.0516 1.0000 0.0067
-11.750 -1.0750 0.02158 0.01695 -0.0515 1.0000 0.0068
-11.500 -1.0528 0.02064 0.01590 -0.0513 1.0000 0.0069
-11.250 -1.0300 0.01975 0.01492 -0.0512 1.0000 0.0069
-11.000 -1.0066 0.01893 0.01401 -0.0511 1.0000 0.0070
-10.750 -0.9827 0.01817 0.01316 -0.0510 1.0000 0.0071
-10.500 -0.9584 0.01745 0.01236 -0.0509 1.0000 0.0072
-10.250 -0.9337 0.01678 0.01162 -0.0508 1.0000 0.0073
-10.000 -0.9088 0.01616 0.01093 -0.0507 1.0000 0.0074
-9.750 -0.8836 0.01558 0.01029 -0.0505 1.0000 0.0076
-9.500 -0.8584 0.01505 0.00970 -0.0504 1.0000 0.0077
-9.250 -0.8334 0.01443 0.00904 -0.0502 1.0000 0.0079
-9.000 -0.8083 0.01393 0.00850 -0.0499 1.0000 0.0082
-8.750 -0.7834 0.01350 0.00805 -0.0496 1.0000 0.0085
-8.500 -0.7526 0.01306 0.00758 -0.0505 0.9978 0.0089
-8.250 -0.7212 0.01264 0.00713 -0.0515 0.9954 0.0092
-8.000 -0.6901 0.01225 0.00670 -0.0524 0.9923 0.0096
-7.750 -0.6590 0.01186 0.00629 -0.0532 0.9884 0.0100
-7.500 -0.6272 0.01153 0.00596 -0.0542 0.9848 0.0105
-7.250 -0.5969 0.01124 0.00566 -0.0549 0.9795 0.0111
-7.000 -0.5661 0.01094 0.00534 -0.0556 0.9744 0.0117
-6.750 -0.5364 0.01066 0.00503 -0.0560 0.9685 0.0122
-6.500 -0.5072 0.01041 0.00478 -0.0563 0.9618 0.0128
-6.250 -0.4788 0.01019 0.00455 -0.0564 0.9547 0.0135
-6.000 -0.4509 0.00998 0.00430 -0.0564 0.9464 0.0143
-5.750 -0.4231 0.00977 0.00407 -0.0563 0.9382 0.0149
-5.500 -0.3955 0.00956 0.00384 -0.0562 0.9299 0.0156
-5.250 -0.3675 0.00937 0.00364 -0.0562 0.9225 0.0163
-5.000 -0.3395 0.00920 0.00343 -0.0561 0.9148 0.0171
-4.750 -0.3113 0.00904 0.00324 -0.0561 0.9080 0.0176
-4.500 -0.2830 0.00883 0.00303 -0.0561 0.9007 0.0185
-4.250 -0.2548 0.00868 0.00284 -0.0561 0.8940 0.0192
-4.000 -0.2260 0.00853 0.00268 -0.0562 0.8878 0.0202
-3.750 -0.1974 0.00838 0.00252 -0.0563 0.8814 0.0211
-3.500 -0.1688 0.00823 0.00236 -0.0564 0.8754 0.0227
-3.250 -0.1398 0.00810 0.00223 -0.0565 0.8683 0.0241
-3.000 -0.1115 0.00798 0.00207 -0.0564 0.8578 0.0260
-2.750 -0.0827 0.00786 0.00194 -0.0565 0.8468 0.0281
-2.500 -0.0540 0.00774 0.00182 -0.0565 0.8356 0.0325
-2.250 -0.0251 0.00758 0.00171 -0.0567 0.8267 0.0468
-2.000 0.0040 0.00743 0.00161 -0.0569 0.8194 0.0655
-1.750 0.0327 0.00724 0.00149 -0.0570 0.8024 0.1011
-1.500 0.0610 0.00705 0.00137 -0.0571 0.7710 0.1569
-1.250 0.0895 0.00672 0.00122 -0.0574 0.7336 0.2576
-1.000 0.1180 0.00633 0.00108 -0.0579 0.6821 0.3945
-0.750 0.1455 0.00626 0.00108 -0.0581 0.5960 0.5116
-0.500 0.1721 0.00670 0.00121 -0.0580 0.4731 0.5635
-0.250 0.1991 0.00718 0.00135 -0.0580 0.3651 0.5876
0.000 0.2266 0.00756 0.00147 -0.0580 0.2827 0.6050
0.250 0.2545 0.00784 0.00156 -0.0580 0.2264 0.6117
0.500 0.2825 0.00810 0.00163 -0.0580 0.1836 0.6159
0.750 0.3107 0.00832 0.00170 -0.0580 0.1512 0.6197
1.000 0.3392 0.00847 0.00178 -0.0580 0.1340 0.6235
1.500 0.3961 0.00871 0.00194 -0.0581 0.1150 0.6316
1.750 0.4245 0.00885 0.00203 -0.0581 0.1089 0.6356
2.000 0.4531 0.00896 0.00211 -0.0581 0.1051 0.6391
2.250 0.4815 0.00906 0.00221 -0.0581 0.1014 0.6430
2.500 0.5099 0.00918 0.00232 -0.0581 0.0975 0.6467
2.750 0.5382 0.00931 0.00243 -0.0581 0.0943 0.6506
3.000 0.5665 0.00942 0.00253 -0.0581 0.0917 0.6542
3.250 0.5947 0.00957 0.00265 -0.0580 0.0870 0.6572
3.500 0.6228 0.00970 0.00277 -0.0580 0.0825 0.6608
3.750 0.6508 0.00984 0.00290 -0.0580 0.0779 0.6646
4.000 0.6787 0.01000 0.00304 -0.0579 0.0736 0.6684
4.250 0.7067 0.01015 0.00318 -0.0579 0.0695 0.6718
4.750 0.7621 0.01050 0.00350 -0.0577 0.0609 0.6792
5.000 0.7896 0.01069 0.00368 -0.0576 0.0566 0.6833
5.500 0.8443 0.01112 0.00408 -0.0573 0.0484 0.6910
5.750 0.8714 0.01135 0.00431 -0.0572 0.0452 0.6949
6.000 0.8985 0.01158 0.00454 -0.0570 0.0423 0.6997
6.250 0.9255 0.01182 0.00479 -0.0568 0.0396 0.7048
6.500 0.9523 0.01208 0.00505 -0.0566 0.0369 0.7095
6.750 0.9790 0.01233 0.00532 -0.0564 0.0344 0.7144
7.000 1.0055 0.01261 0.00561 -0.0562 0.0319 0.7201
7.250 1.0319 0.01289 0.00591 -0.0559 0.0299 0.7259
7.500 1.0581 0.01319 0.00623 -0.0556 0.0281 0.7327
7.750 1.0842 0.01349 0.00657 -0.0553 0.0268 0.7410
8.000 1.1102 0.01380 0.00691 -0.0550 0.0256 0.7497
8.250 1.1359 0.01414 0.00729 -0.0547 0.0245 0.7600
8.500 1.1614 0.01449 0.00769 -0.0543 0.0238 0.7714
8.750 1.1869 0.01480 0.00808 -0.0539 0.0233 0.7855
9.000 1.2121 0.01511 0.00848 -0.0535 0.0227 0.8050
9.250 1.2365 0.01541 0.00891 -0.0530 0.0222 0.8399
9.500 1.2563 0.01550 0.00928 -0.0512 0.0218 1.0000
9.750 1.2809 0.01596 0.00976 -0.0508 0.0213 1.0000
10.000 1.3050 0.01647 0.01030 -0.0503 0.0209 1.0000
10.250 1.3290 0.01696 0.01083 -0.0498 0.0206 1.0000
10.500 1.3531 0.01741 0.01133 -0.0492 0.0203 1.0000
10.750 1.3769 0.01789 0.01184 -0.0487 0.0200 1.0000
11.000 1.4004 0.01838 0.01239 -0.0481 0.0197 1.0000
11.250 1.4234 0.01889 0.01295 -0.0475 0.0194 1.0000
11.500 1.4460 0.01944 0.01355 -0.0468 0.0192 1.0000
11.750 1.4681 0.02002 0.01418 -0.0460 0.0189 1.0000
12.000 1.4896 0.02062 0.01483 -0.0452 0.0187 1.0000
12.250 1.5105 0.02126 0.01553 -0.0443 0.0185 1.0000
12.500 1.5306 0.02196 0.01628 -0.0434 0.0183 1.0000
12.750 1.5497 0.02272 0.01711 -0.0423 0.0181 1.0000
13.000 1.5672 0.02358 0.01803 -0.0410 0.0178 1.0000
13.250 1.5839 0.02446 0.01899 -0.0396 0.0177 1.0000
13.500 1.6011 0.02522 0.01983 -0.0383 0.0176 1.0000
13.750 1.6172 0.02602 0.02073 -0.0368 0.0175 1.0000
14.000 1.6316 0.02688 0.02167 -0.0352 0.0174 1.0000
14.250 1.6430 0.02777 0.02265 -0.0331 0.0173 1.0000
14.500 1.6516 0.02873 0.02370 -0.0306 0.0172 1.0000
14.750 1.6591 0.02981 0.02488 -0.0282 0.0171 1.0000
15.000 1.6657 0.03101 0.02618 -0.0260 0.0170 1.0000
15.250 1.6712 0.03235 0.02762 -0.0239 0.0169 1.0000
15.500 1.6755 0.03386 0.02923 -0.0220 0.0168 1.0000
15.750 1.6789 0.03554 0.03102 -0.0202 0.0167 1.0000
16.000 1.6804 0.03746 0.03306 -0.0187 0.0166 1.0000
16.250 1.6807 0.03963 0.03534 -0.0174 0.0165 1.0000
16.500 1.6793 0.04208 0.03791 -0.0165 0.0164 1.0000
16.750 1.6761 0.04490 0.04085 -0.0159 0.0163 1.0000
17.000 1.6715 0.04806 0.04414 -0.0158 0.0162 1.0000
17.250 1.6638 0.05183 0.04804 -0.0162 0.0161 1.0000
17.500 1.6520 0.05649 0.05284 -0.0175 0.0161 1.0000
17.750 1.6301 0.06316 0.05970 -0.0204 0.0161 1.0000
18.000 1.6024 0.07187 0.06861 -0.0254 0.0161 1.0000
18.250 1.5387 0.08912 0.08619 -0.0364 0.0162 1.0000
18.500 1.4133 0.11862 0.11607 -0.0533 0.0165 1.0000
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Polar data table (+)
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