RAF 28 AIRFOIL (raf28-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 28 AIRFOIL (raf28-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.93 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf28-il-1000000.txt Download as CSV file: xf-raf28-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 28 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8996 0.06434 0.06240 -0.0421 1.0000 0.0085
-13.500 -0.9180 0.05537 0.05333 -0.0487 1.0000 0.0084
-13.250 -0.9430 0.04438 0.04212 -0.0598 1.0000 0.0084
-13.000 -0.5482 0.13094 0.12919 -0.0093 1.0000 0.0115
-12.750 -0.9876 0.03470 0.03203 -0.0633 1.0000 0.0083
-12.500 -0.9990 0.03281 0.03001 -0.0596 1.0000 0.0083
-12.250 -1.0257 0.02877 0.02558 -0.0548 1.0000 0.0085
-12.000 -1.0320 0.02608 0.02263 -0.0513 1.0000 0.0088
-11.750 -1.0232 0.02474 0.02116 -0.0491 1.0000 0.0090
-11.500 -1.0099 0.02379 0.02012 -0.0473 1.0000 0.0092
-11.250 -0.9937 0.02312 0.01938 -0.0457 1.0000 0.0095
-11.000 -0.9764 0.02254 0.01873 -0.0443 1.0000 0.0098
-10.750 -0.9600 0.02182 0.01791 -0.0427 1.0000 0.0101
-10.500 -0.9431 0.02112 0.01711 -0.0411 1.0000 0.0105
-10.250 -0.9263 0.02038 0.01626 -0.0395 1.0000 0.0108
-10.000 -0.9080 0.01980 0.01558 -0.0380 1.0000 0.0111
-9.750 -0.8951 0.01845 0.01404 -0.0358 1.0000 0.0115
-9.500 -0.8797 0.01746 0.01296 -0.0339 1.0000 0.0121
-9.250 -0.8591 0.01718 0.01265 -0.0327 1.0000 0.0125
-9.000 -0.8383 0.01696 0.01241 -0.0315 1.0000 0.0130
-8.750 -0.8119 0.01653 0.01192 -0.0315 0.9994 0.0136
-8.500 -0.7775 0.01597 0.01127 -0.0333 0.9976 0.0143
-8.250 -0.7421 0.01573 0.01095 -0.0351 0.9958 0.0148
-8.000 -0.7109 0.01451 0.00961 -0.0365 0.9939 0.0159
-7.750 -0.6778 0.01443 0.00955 -0.0378 0.9913 0.0166
-7.500 -0.6438 0.01424 0.00934 -0.0393 0.9886 0.0176
-7.250 -0.6094 0.01390 0.00894 -0.0409 0.9862 0.0185
-7.000 -0.5734 0.01374 0.00873 -0.0427 0.9842 0.0193
-6.750 -0.5464 0.01256 0.00745 -0.0429 0.9790 0.0206
-6.500 -0.5141 0.01215 0.00705 -0.0441 0.9745 0.0217
-6.250 -0.4792 0.01184 0.00672 -0.0458 0.9713 0.0229
-6.000 -0.4497 0.01146 0.00630 -0.0462 0.9621 0.0240
-5.750 -0.4118 0.01112 0.00592 -0.0485 0.9572 0.0251
-5.500 -0.3751 0.01105 0.00582 -0.0504 0.9463 0.0257
-5.250 -0.3415 0.00979 0.00443 -0.0521 0.9314 0.0277
-5.000 -0.3077 0.00935 0.00391 -0.0534 0.9108 0.0289
-4.750 -0.2792 0.00911 0.00356 -0.0536 0.8888 0.0302
-4.500 -0.2533 0.00890 0.00325 -0.0531 0.8719 0.0314
-4.250 -0.2277 0.00870 0.00295 -0.0526 0.8589 0.0323
-4.000 -0.2020 0.00853 0.00271 -0.0521 0.8486 0.0330
-3.750 -0.1760 0.00841 0.00252 -0.0516 0.8395 0.0337
-3.500 -0.1502 0.00822 0.00226 -0.0511 0.8312 0.0345
-3.250 -0.1244 0.00802 0.00198 -0.0506 0.8237 0.0363
-3.000 -0.0982 0.00786 0.00179 -0.0502 0.8160 0.0388
-2.750 -0.0720 0.00773 0.00164 -0.0498 0.8090 0.0423
-2.500 -0.0463 0.00751 0.00149 -0.0493 0.8013 0.0652
-2.250 -0.0217 0.00718 0.00135 -0.0487 0.7941 0.1235
-2.000 0.0017 0.00671 0.00122 -0.0479 0.7861 0.2201
-1.750 0.0268 0.00647 0.00115 -0.0474 0.7785 0.2810
-1.500 0.0524 0.00629 0.00109 -0.0469 0.7699 0.3265
-1.250 0.0779 0.00610 0.00104 -0.0465 0.7608 0.3737
-1.000 0.1027 0.00590 0.00100 -0.0458 0.7511 0.4336
-0.750 0.1271 0.00565 0.00095 -0.0451 0.7398 0.5074
-0.500 0.1503 0.00536 0.00092 -0.0442 0.7272 0.5935
-0.250 0.1726 0.00511 0.00092 -0.0429 0.7131 0.6856
0.250 0.2155 0.00474 0.00093 -0.0398 0.6787 0.8350
0.500 0.2455 0.00464 0.00102 -0.0399 0.6606 0.9168
0.750 0.2915 0.00478 0.00114 -0.0438 0.6440 0.9562
1.000 0.3288 0.00493 0.00121 -0.0458 0.6250 0.9682
1.250 0.3649 0.00510 0.00127 -0.0476 0.6059 0.9734
1.500 0.4001 0.00522 0.00134 -0.0491 0.5918 0.9787
1.750 0.4328 0.00533 0.00141 -0.0502 0.5795 0.9838
2.000 0.4705 0.00545 0.00146 -0.0524 0.5624 0.9866
2.250 0.5063 0.00557 0.00152 -0.0542 0.5408 0.9900
2.500 0.5405 0.00570 0.00158 -0.0556 0.5222 0.9934
2.750 0.5764 0.00585 0.00164 -0.0575 0.4961 0.9958
3.000 0.6146 0.00603 0.00170 -0.0599 0.4642 0.9988
3.250 0.6454 0.00621 0.00178 -0.0607 0.4355 1.0000
3.500 0.6670 0.00642 0.00187 -0.0595 0.4043 1.0000
3.750 0.6883 0.00668 0.00198 -0.0582 0.3690 1.0000
4.000 0.7077 0.00708 0.00215 -0.0566 0.3138 1.0000
4.250 0.7244 0.00769 0.00242 -0.0545 0.2376 1.0000
4.500 0.7404 0.00838 0.00275 -0.0524 0.1627 1.0000
4.750 0.7588 0.00889 0.00305 -0.0507 0.1190 1.0000
5.000 0.7785 0.00930 0.00333 -0.0491 0.0890 1.0000
5.250 0.7946 0.01001 0.00376 -0.0470 0.0383 1.0000
5.500 0.8152 0.01037 0.00410 -0.0455 0.0312 1.0000
5.750 0.8371 0.01063 0.00439 -0.0443 0.0286 1.0000
6.000 0.8573 0.01103 0.00479 -0.0428 0.0250 1.0000
6.250 0.8782 0.01138 0.00518 -0.0415 0.0229 1.0000
6.500 0.8999 0.01166 0.00548 -0.0403 0.0212 1.0000
6.750 0.9209 0.01199 0.00580 -0.0390 0.0194 1.0000
7.000 0.9387 0.01259 0.00647 -0.0371 0.0176 1.0000
7.250 0.9603 0.01288 0.00678 -0.0360 0.0168 1.0000
7.500 0.9812 0.01323 0.00715 -0.0347 0.0158 1.0000
7.750 1.0017 0.01360 0.00754 -0.0334 0.0149 1.0000
8.000 1.0201 0.01413 0.00809 -0.0317 0.0140 1.0000
8.250 1.0352 0.01490 0.00895 -0.0295 0.0131 1.0000
8.500 1.0553 0.01528 0.00937 -0.0281 0.0126 1.0000
8.750 1.0742 0.01575 0.00987 -0.0266 0.0121 1.0000
9.000 1.0922 0.01627 0.01044 -0.0250 0.0116 1.0000
9.250 1.1107 0.01673 0.01093 -0.0235 0.0111 1.0000
9.500 1.1273 0.01731 0.01154 -0.0217 0.0106 1.0000
9.750 1.1398 0.01818 0.01248 -0.0192 0.0102 1.0000
10.000 1.1445 0.01964 0.01406 -0.0156 0.0097 1.0000
10.250 1.1572 0.02034 0.01484 -0.0132 0.0096 1.0000
10.500 1.1696 0.02093 0.01549 -0.0108 0.0093 1.0000
10.750 1.1808 0.02164 0.01627 -0.0083 0.0091 1.0000
11.000 1.1918 0.02240 0.01710 -0.0059 0.0088 1.0000
11.250 1.2011 0.02334 0.01814 -0.0034 0.0086 1.0000
11.500 1.2146 0.02390 0.01875 -0.0017 0.0082 1.0000
11.750 1.2255 0.02472 0.01963 0.0002 0.0080 1.0000
12.000 1.2319 0.02601 0.02103 0.0025 0.0080 1.0000
12.250 1.2432 0.02680 0.02184 0.0040 0.0076 1.0000
12.500 1.2452 0.02855 0.02369 0.0061 0.0074 1.0000
12.750 1.2444 0.03070 0.02599 0.0082 0.0072 1.0000
13.000 1.2340 0.03407 0.02959 0.0105 0.0070 1.0000
13.250 1.2332 0.03647 0.03213 0.0119 0.0070 1.0000
13.500 1.2371 0.03831 0.03410 0.0126 0.0069 1.0000
13.750 1.2406 0.04030 0.03621 0.0132 0.0068 1.0000
14.000 1.2369 0.04322 0.03928 0.0136 0.0068 1.0000
14.250 1.2365 0.04588 0.04208 0.0136 0.0067 1.0000
14.500 1.2279 0.04968 0.04605 0.0134 0.0067 1.0000
14.750 1.2179 0.05387 0.05041 0.0126 0.0066 1.0000
15.000 1.2081 0.05819 0.05489 0.0114 0.0066 1.0000
15.250 1.2003 0.06250 0.05932 0.0098 0.0065 1.0000
15.500 1.1862 0.06791 0.06490 0.0077 0.0064 1.0000
15.750 1.1655 0.07476 0.07192 0.0046 0.0065 1.0000
16.000 1.1411 0.08273 0.08008 0.0007 0.0065 1.0000
16.250 1.1266 0.08937 0.08685 -0.0029 0.0064 1.0000
16.500 1.0996 0.09866 0.09630 -0.0079 0.0066 1.0000
16.750 1.0801 0.10705 0.10483 -0.0125 0.0065 1.0000
17.000 1.0478 0.11874 0.11666 -0.0190 0.0066 1.0000
17.250 1.0004 0.13502 0.13313 -0.0279 0.0068 1.0000
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