RAF 34 AIRFOIL (raf34-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 34 AIRFOIL (raf34-il) Reynolds number: 500,000 Max Cl/Cd: 79.36 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf34-il-500000-n5.txt Download as CSV file: xf-raf34-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.9763 0.06744 0.06444 -0.0409 1.0000 0.0162
-15.250 -1.0387 0.05217 0.04876 -0.0525 1.0000 0.0160
-15.000 -1.0396 0.04869 0.04519 -0.0548 1.0000 0.0163
-14.750 -1.0476 0.04478 0.04113 -0.0567 1.0000 0.0165
-14.500 -1.0548 0.04148 0.03768 -0.0576 1.0000 0.0167
-14.250 -1.0588 0.03888 0.03495 -0.0575 1.0000 0.0169
-14.000 -1.0634 0.03648 0.03238 -0.0566 1.0000 0.0172
-13.750 -1.0643 0.03460 0.03034 -0.0552 1.0000 0.0176
-13.500 -1.0644 0.03288 0.02845 -0.0533 1.0000 0.0179
-13.250 -1.0635 0.03130 0.02670 -0.0510 1.0000 0.0182
-13.000 -1.0589 0.03007 0.02529 -0.0487 1.0000 0.0185
-12.750 -1.0547 0.02892 0.02406 -0.0461 1.0000 0.0188
-12.500 -1.0457 0.02824 0.02334 -0.0438 1.0000 0.0191
-12.250 -1.0359 0.02766 0.02271 -0.0413 1.0000 0.0193
-12.000 -1.0246 0.02717 0.02218 -0.0390 1.0000 0.0197
-11.750 -1.0116 0.02653 0.02147 -0.0369 1.0000 0.0200
-11.500 -0.9972 0.02591 0.02078 -0.0351 1.0000 0.0205
-11.250 -0.9829 0.02517 0.01994 -0.0332 1.0000 0.0209
-11.000 -0.9677 0.02444 0.01910 -0.0315 1.0000 0.0214
-10.750 -0.9520 0.02370 0.01824 -0.0297 1.0000 0.0219
-10.500 -0.9351 0.02307 0.01750 -0.0280 1.0000 0.0224
-10.250 -0.9177 0.02248 0.01679 -0.0264 1.0000 0.0228
-10.000 -0.9008 0.02177 0.01597 -0.0247 1.0000 0.0231
-9.750 -0.8766 0.02067 0.01481 -0.0248 0.9823 0.0237
-9.500 -0.8304 0.01984 0.01392 -0.0294 0.9421 0.0244
-9.250 -0.7860 0.01912 0.01307 -0.0334 0.9084 0.0251
-9.000 -0.7598 0.01860 0.01238 -0.0334 0.8779 0.0257
-8.750 -0.7383 0.01813 0.01176 -0.0323 0.8550 0.0262
-8.500 -0.7170 0.01771 0.01120 -0.0311 0.8371 0.0268
-8.250 -0.6953 0.01729 0.01064 -0.0300 0.8218 0.0273
-8.000 -0.6733 0.01685 0.01008 -0.0289 0.8081 0.0277
-7.750 -0.6509 0.01643 0.00954 -0.0279 0.7956 0.0280
-7.500 -0.6283 0.01604 0.00904 -0.0269 0.7838 0.0283
-7.250 -0.6069 0.01544 0.00835 -0.0258 0.7726 0.0288
-7.000 -0.5854 0.01486 0.00771 -0.0247 0.7619 0.0295
-6.750 -0.5629 0.01444 0.00721 -0.0237 0.7519 0.0300
-6.500 -0.5398 0.01406 0.00677 -0.0228 0.7417 0.0305
-6.250 -0.5164 0.01371 0.00635 -0.0219 0.7323 0.0310
-6.000 -0.4927 0.01339 0.00596 -0.0211 0.7231 0.0315
-5.750 -0.4686 0.01308 0.00559 -0.0203 0.7141 0.0321
-5.500 -0.4445 0.01281 0.00525 -0.0195 0.7056 0.0327
-5.250 -0.4199 0.01254 0.00493 -0.0189 0.6971 0.0334
-5.000 -0.3952 0.01232 0.00462 -0.0182 0.6891 0.0340
-4.750 -0.3700 0.01210 0.00435 -0.0176 0.6811 0.0347
-4.500 -0.3453 0.01186 0.00406 -0.0169 0.6736 0.0353
-4.250 -0.3203 0.01160 0.00375 -0.0163 0.6660 0.0365
-4.000 -0.2952 0.01140 0.00351 -0.0157 0.6590 0.0378
-3.750 -0.2696 0.01121 0.00330 -0.0151 0.6518 0.0393
-3.500 -0.2440 0.01105 0.00309 -0.0146 0.6447 0.0412
-3.250 -0.2183 0.01089 0.00291 -0.0141 0.6381 0.0444
-3.000 -0.1931 0.01067 0.00272 -0.0135 0.6310 0.0536
-2.750 -0.1689 0.01039 0.00256 -0.0128 0.6247 0.0858
-2.500 -0.1434 0.01019 0.00244 -0.0123 0.6180 0.1069
-2.250 -0.1180 0.01004 0.00232 -0.0118 0.6113 0.1255
-2.000 -0.0924 0.00987 0.00220 -0.0113 0.6050 0.1466
-1.750 -0.0677 0.00963 0.00209 -0.0107 0.5981 0.1820
-1.500 -0.0435 0.00938 0.00200 -0.0100 0.5918 0.2346
-1.250 -0.0187 0.00916 0.00192 -0.0094 0.5850 0.2800
-1.000 0.0051 0.00890 0.00183 -0.0086 0.5787 0.3362
-0.750 0.0258 0.00841 0.00173 -0.0073 0.5722 0.4430
-0.500 0.0456 0.00799 0.00167 -0.0057 0.5656 0.5494
-0.250 0.0654 0.00766 0.00163 -0.0039 0.5595 0.6372
0.000 0.0854 0.00737 0.00164 -0.0021 0.5526 0.7189
0.250 0.1076 0.00719 0.00167 -0.0006 0.5461 0.7872
0.500 0.1348 0.00709 0.00172 -0.0002 0.5386 0.8341
0.750 0.1662 0.00709 0.00178 -0.0007 0.5304 0.8688
1.000 0.2051 0.00715 0.00188 -0.0029 0.5191 0.8987
1.250 0.2463 0.00729 0.00198 -0.0056 0.5054 0.9170
1.500 0.2846 0.00742 0.00206 -0.0078 0.4928 0.9261
1.750 0.3183 0.00755 0.00213 -0.0090 0.4830 0.9335
2.000 0.3542 0.00767 0.00221 -0.0106 0.4729 0.9386
2.250 0.3829 0.00780 0.00230 -0.0107 0.4632 0.9471
2.500 0.4184 0.00797 0.00242 -0.0123 0.4526 0.9508
2.750 0.4501 0.00810 0.00252 -0.0131 0.4423 0.9556
3.000 0.4776 0.00824 0.00262 -0.0130 0.4324 0.9609
3.250 0.5114 0.00839 0.00272 -0.0143 0.4196 0.9630
3.500 0.5438 0.00855 0.00283 -0.0154 0.4072 0.9659
3.750 0.5739 0.00868 0.00295 -0.0159 0.3974 0.9698
4.000 0.6031 0.00884 0.00308 -0.0162 0.3870 0.9736
4.250 0.6367 0.00901 0.00321 -0.0176 0.3749 0.9756
4.500 0.6692 0.00917 0.00334 -0.0187 0.3626 0.9782
4.750 0.6993 0.00935 0.00349 -0.0193 0.3494 0.9814
5.000 0.7283 0.00958 0.00367 -0.0198 0.3328 0.9845
5.250 0.7604 0.00983 0.00383 -0.0210 0.3130 0.9862
5.500 0.7918 0.01007 0.00401 -0.0220 0.2947 0.9884
5.750 0.8217 0.01038 0.00424 -0.0227 0.2712 0.9908
6.000 0.8502 0.01073 0.00449 -0.0233 0.2468 0.9932
6.250 0.8801 0.01109 0.00476 -0.0241 0.2230 0.9951
6.500 0.9093 0.01157 0.00509 -0.0250 0.1897 0.9972
6.750 0.9370 0.01222 0.00553 -0.0257 0.1498 0.9992
7.000 0.9603 0.01269 0.00591 -0.0253 0.1321 1.0000
7.250 0.9782 0.01310 0.00628 -0.0236 0.1217 1.0000
7.500 0.9967 0.01344 0.00662 -0.0221 0.1137 1.0000
7.750 1.0145 0.01383 0.00699 -0.0204 0.1062 1.0000
8.000 1.0321 0.01422 0.00736 -0.0188 0.0956 1.0000
8.250 1.0479 0.01470 0.00777 -0.0168 0.0757 1.0000
8.500 1.0576 0.01554 0.00842 -0.0140 0.0515 1.0000
8.750 1.0716 0.01607 0.00895 -0.0118 0.0448 1.0000
9.000 1.0853 0.01659 0.00947 -0.0096 0.0402 1.0000
9.250 1.0993 0.01707 0.00997 -0.0074 0.0372 1.0000
9.500 1.1113 0.01762 0.01054 -0.0049 0.0346 1.0000
9.750 1.1237 0.01813 0.01109 -0.0025 0.0325 1.0000
10.000 1.1350 0.01864 0.01164 0.0001 0.0307 1.0000
10.250 1.1399 0.01921 0.01223 0.0037 0.0288 1.0000
10.500 1.1427 0.01985 0.01289 0.0076 0.0274 1.0000
10.750 1.1504 0.02044 0.01355 0.0103 0.0263 1.0000
11.000 1.1577 0.02118 0.01434 0.0128 0.0249 1.0000
11.250 1.1648 0.02206 0.01527 0.0150 0.0236 1.0000
11.500 1.1704 0.02317 0.01641 0.0170 0.0222 1.0000
11.750 1.1790 0.02420 0.01751 0.0185 0.0212 1.0000
12.000 1.1874 0.02534 0.01871 0.0198 0.0202 1.0000
12.250 1.1952 0.02660 0.02003 0.0209 0.0192 1.0000
12.500 1.2015 0.02806 0.02152 0.0220 0.0181 1.0000
12.750 1.2067 0.02970 0.02322 0.0229 0.0174 1.0000
13.000 1.2132 0.03129 0.02490 0.0236 0.0167 1.0000
13.250 1.2186 0.03303 0.02672 0.0242 0.0163 1.0000
13.500 1.2237 0.03487 0.02862 0.0247 0.0155 1.0000
13.750 1.2277 0.03686 0.03066 0.0251 0.0148 1.0000
14.000 1.2295 0.03910 0.03296 0.0254 0.0143 1.0000
14.250 1.2297 0.04159 0.03552 0.0256 0.0138 1.0000
14.500 1.2305 0.04406 0.03809 0.0256 0.0136 1.0000
14.750 1.2332 0.04637 0.04049 0.0256 0.0130 1.0000
15.000 1.2333 0.04903 0.04324 0.0254 0.0128 1.0000
15.250 1.2328 0.05186 0.04616 0.0251 0.0125 1.0000
15.500 1.2306 0.05499 0.04938 0.0247 0.0122 1.0000
15.750 1.2289 0.05813 0.05261 0.0241 0.0119 1.0000
16.000 1.2269 0.06141 0.05597 0.0233 0.0117 1.0000
16.250 1.2225 0.06506 0.05970 0.0224 0.0114 1.0000
16.500 1.2182 0.06882 0.06354 0.0214 0.0112 1.0000
16.750 1.2113 0.07299 0.06780 0.0201 0.0110 1.0000
17.000 1.2032 0.07741 0.07231 0.0187 0.0108 1.0000
17.250 1.1979 0.08153 0.07652 0.0174 0.0107 1.0000
17.500 1.1928 0.08568 0.08078 0.0159 0.0105 1.0000
17.750 1.1869 0.08998 0.08518 0.0144 0.0104 1.0000
18.000 1.1801 0.09449 0.08979 0.0128 0.0103 1.0000
18.250 1.1753 0.09879 0.09420 0.0111 0.0100 1.0000
18.500 1.1674 0.10359 0.09910 0.0092 0.0099 1.0000
18.750 1.1616 0.10814 0.10374 0.0074 0.0097 1.0000
19.000 1.1524 0.11326 0.10896 0.0052 0.0097 1.0000
19.250 1.1463 0.11801 0.11380 0.0031 0.0094 1.0000
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