RAF 34 AIRFOIL (raf34-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 34 AIRFOIL (raf34-il) Reynolds number: 50,000 Max Cl/Cd: 30.69 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf34-il-50000-n5.txt Download as CSV file: xf-raf34-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 34 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5259 0.09777 0.09043 -0.0283 1.0000 0.0725
-10.500 -0.5328 0.09183 0.08454 -0.0317 1.0000 0.0723
-10.250 -0.5434 0.08519 0.07793 -0.0360 1.0000 0.0719
-10.000 -0.5599 0.07900 0.07176 -0.0398 1.0000 0.0715
-9.750 -0.5798 0.07374 0.06648 -0.0418 1.0000 0.0710
-9.500 -0.6019 0.06933 0.06202 -0.0416 1.0000 0.0707
-9.250 -0.6210 0.06533 0.05792 -0.0403 1.0000 0.0704
-9.000 -0.6354 0.06137 0.05378 -0.0387 1.0000 0.0703
-8.750 -0.6452 0.05761 0.04979 -0.0368 1.0000 0.0704
-8.500 -0.6509 0.05409 0.04600 -0.0347 1.0000 0.0705
-8.250 -0.6540 0.05078 0.04236 -0.0322 1.0000 0.0711
-8.000 -0.6553 0.04776 0.03892 -0.0294 1.0000 0.0722
-7.750 -0.6519 0.04518 0.03605 -0.0268 1.0000 0.0735
-7.500 -0.6421 0.04335 0.03415 -0.0248 1.0000 0.0750
-7.250 -0.6340 0.04155 0.03219 -0.0224 1.0000 0.0763
-7.000 -0.6270 0.03975 0.03021 -0.0197 1.0000 0.0772
-6.750 -0.6213 0.03815 0.02841 -0.0166 1.0000 0.0782
-6.500 -0.6160 0.03673 0.02677 -0.0135 1.0000 0.0793
-6.250 -0.6005 0.03514 0.02490 -0.0122 0.9960 0.0810
-6.000 -0.5639 0.03325 0.02252 -0.0145 0.9836 0.0850
-5.750 -0.5269 0.03174 0.02094 -0.0169 0.9720 0.0893
-5.500 -0.4889 0.03032 0.01936 -0.0192 0.9607 0.0938
-5.250 -0.4488 0.02894 0.01767 -0.0215 0.9504 0.0992
-5.000 -0.4078 0.02769 0.01646 -0.0242 0.9415 0.1070
-4.750 -0.3680 0.02661 0.01534 -0.0267 0.9316 0.1206
-4.500 -0.3305 0.02551 0.01423 -0.0288 0.9212 0.1405
-4.250 -0.2927 0.02436 0.01318 -0.0310 0.9121 0.1742
-4.000 -0.2628 0.02344 0.01255 -0.0320 0.9001 0.2238
-3.750 -0.2372 0.02243 0.01203 -0.0322 0.8883 0.3098
-3.500 -0.2175 0.02121 0.01170 -0.0309 0.8773 0.4428
-3.250 -0.1852 0.02051 0.01187 -0.0301 0.8681 0.6349
-3.000 -0.1337 0.02070 0.01216 -0.0323 0.8599 0.7575
-2.750 -0.0863 0.02105 0.01229 -0.0342 0.8513 0.8199
-2.500 -0.0357 0.02152 0.01251 -0.0369 0.8415 0.8644
-2.250 0.0309 0.02205 0.01272 -0.0422 0.8341 0.9068
-2.000 0.0846 0.02227 0.01268 -0.0465 0.8234 0.9354
-1.750 0.1314 0.02225 0.01242 -0.0502 0.8126 0.9541
-1.500 0.1854 0.02209 0.01203 -0.0553 0.8030 0.9754
-1.250 0.2429 0.02173 0.01149 -0.0616 0.7913 0.9961
-1.000 0.2693 0.02166 0.01128 -0.0620 0.7797 1.0000
-0.750 0.2880 0.02167 0.01116 -0.0608 0.7690 1.0000
-0.500 0.3062 0.02173 0.01113 -0.0595 0.7576 1.0000
-0.250 0.3244 0.02182 0.01115 -0.0583 0.7463 1.0000
0.000 0.3436 0.02189 0.01111 -0.0569 0.7365 1.0000
0.250 0.3621 0.02201 0.01117 -0.0556 0.7257 1.0000
0.500 0.3809 0.02216 0.01127 -0.0543 0.7150 1.0000
0.750 0.4019 0.02222 0.01123 -0.0530 0.7063 1.0000
1.000 0.4204 0.02245 0.01146 -0.0518 0.6949 1.0000
1.250 0.4399 0.02263 0.01160 -0.0505 0.6850 1.0000
1.500 0.4601 0.02278 0.01170 -0.0491 0.6758 1.0000
1.750 0.4785 0.02307 0.01199 -0.0477 0.6651 1.0000
2.000 0.4992 0.02322 0.01209 -0.0464 0.6566 1.0000
2.250 0.5177 0.02352 0.01241 -0.0449 0.6460 1.0000
2.500 0.5368 0.02382 0.01271 -0.0435 0.6363 1.0000
2.750 0.5575 0.02400 0.01288 -0.0421 0.6275 1.0000
3.000 0.5754 0.02441 0.01332 -0.0406 0.6168 1.0000
3.250 0.5968 0.02458 0.01348 -0.0392 0.6087 1.0000
3.500 0.6147 0.02500 0.01397 -0.0377 0.5979 1.0000
3.750 0.6336 0.02538 0.01439 -0.0362 0.5882 1.0000
4.000 0.6547 0.02560 0.01463 -0.0348 0.5796 1.0000
4.250 0.6717 0.02612 0.01524 -0.0332 0.5688 1.0000
4.500 0.6936 0.02633 0.01547 -0.0319 0.5606 1.0000
4.750 0.7110 0.02683 0.01606 -0.0303 0.5500 1.0000
5.000 0.7290 0.02731 0.01664 -0.0287 0.5401 1.0000
5.250 0.7514 0.02749 0.01685 -0.0274 0.5316 1.0000
5.500 0.7670 0.02809 0.01757 -0.0256 0.5201 1.0000
5.750 0.7857 0.02844 0.01799 -0.0239 0.5093 1.0000
6.000 0.8090 0.02839 0.01798 -0.0224 0.4988 1.0000
6.250 0.8263 0.02865 0.01833 -0.0205 0.4852 1.0000
6.500 0.8433 0.02886 0.01862 -0.0184 0.4709 1.0000
6.750 0.8603 0.02908 0.01892 -0.0164 0.4565 1.0000
7.000 0.8769 0.02942 0.01937 -0.0144 0.4431 1.0000
7.250 0.8942 0.02981 0.01986 -0.0126 0.4310 1.0000
7.500 0.9131 0.03008 0.02022 -0.0109 0.4190 1.0000
7.750 0.9316 0.03036 0.02058 -0.0091 0.4063 1.0000
8.000 0.9448 0.03097 0.02135 -0.0069 0.3926 1.0000
8.250 0.9580 0.03160 0.02212 -0.0047 0.3791 1.0000
8.500 0.9714 0.03221 0.02286 -0.0026 0.3652 1.0000
8.750 0.9834 0.03272 0.02344 -0.0001 0.3489 1.0000
9.000 0.9938 0.03305 0.02376 0.0027 0.3298 1.0000
9.250 0.9945 0.03389 0.02466 0.0061 0.3087 1.0000
9.500 0.9942 0.03473 0.02546 0.0095 0.2870 1.0000
9.750 0.9911 0.03570 0.02634 0.0132 0.2672 1.0000
10.000 0.9863 0.03709 0.02774 0.0163 0.2484 1.0000
10.250 0.9831 0.03868 0.02932 0.0187 0.2301 1.0000
10.500 0.9807 0.04046 0.03108 0.0207 0.2126 1.0000
10.750 0.9778 0.04247 0.03305 0.0222 0.1958 1.0000
11.000 0.9740 0.04472 0.03524 0.0235 0.1796 1.0000
11.250 0.9694 0.04722 0.03764 0.0245 0.1643 1.0000
11.500 0.9646 0.04994 0.04032 0.0253 0.1500 1.0000
11.750 0.9600 0.05276 0.04306 0.0259 0.1374 1.0000
12.000 0.9560 0.05572 0.04599 0.0264 0.1253 1.0000
12.250 0.9534 0.05865 0.04891 0.0268 0.1151 1.0000
12.500 0.9516 0.06145 0.05158 0.0272 0.1067 1.0000
12.750 0.9509 0.06449 0.05480 0.0274 0.0985 1.0000
13.000 0.9510 0.06726 0.05752 0.0275 0.0924 1.0000
13.250 0.9501 0.07051 0.06098 0.0273 0.0865 1.0000
13.500 0.9511 0.07328 0.06374 0.0273 0.0820 1.0000
13.750 0.9505 0.07668 0.06733 0.0270 0.0781 1.0000
14.000 0.9483 0.08025 0.07105 0.0263 0.0744 1.0000
14.250 0.9499 0.08312 0.07393 0.0259 0.0713 1.0000
14.500 0.9464 0.08717 0.07814 0.0250 0.0687 1.0000
14.750 0.9387 0.09219 0.08340 0.0235 0.0668 1.0000
15.000 0.9292 0.09761 0.08904 0.0215 0.0654 1.0000
15.250 0.9167 0.10377 0.09539 0.0190 0.0642 1.0000
15.500 0.9031 0.11031 0.10207 0.0161 0.0629 1.0000
15.750 0.9168 0.11092 0.10252 0.0168 0.0600 1.0000
16.000 0.8932 0.12005 0.11188 0.0121 0.0599 1.0000
16.250 0.8618 0.13177 0.12377 0.0058 0.0600 1.0000
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