RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 32 MOD AIRFOIL (raf32md-il) Reynolds number: 100,000 Max Cl/Cd: 62.1 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf32md-il-100000.txt Download as CSV file: xf-raf32md-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 32 MOD AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3664 0.10733 0.10240 -0.0394 1.0000 0.1094
-9.000 -0.3920 0.10679 0.10201 -0.0402 1.0000 0.1109
-8.750 -0.4217 0.10648 0.10186 -0.0396 1.0000 0.1113
-8.500 -0.3765 0.09977 0.09504 -0.0354 1.0000 0.1168
-8.250 -0.3827 0.09798 0.09331 -0.0336 1.0000 0.1204
-8.000 -0.3994 0.09664 0.09207 -0.0319 1.0000 0.1231
-7.750 -0.4290 0.09616 0.09174 -0.0297 1.0000 0.1247
-7.500 -0.3622 0.08680 0.08277 -0.0241 1.0000 0.1310
-7.250 -0.3700 0.08481 0.08083 -0.0221 1.0000 0.1341
-7.000 -0.4628 0.08951 0.08532 -0.0234 1.0000 0.1296
-6.750 -0.4649 0.08742 0.08326 -0.0212 1.0000 0.1327
-6.500 -0.4743 0.08499 0.08088 -0.0216 1.0000 0.1368
-6.250 -0.4918 0.07987 0.07577 -0.0314 1.0000 0.1420
-6.000 -0.4863 0.07789 0.07384 -0.0257 1.0000 0.1441
-5.750 -0.4845 0.07383 0.06964 -0.0339 1.0000 0.1553
-5.500 -0.4806 0.07024 0.06611 -0.0317 1.0000 0.1578
-5.250 -0.4743 0.06837 0.06428 -0.0282 1.0000 0.1613
-5.000 -0.4422 0.06280 0.05838 -0.0409 0.9953 0.1862
-4.750 -0.4200 0.06037 0.05606 -0.0387 0.9907 0.1909
-4.500 -0.3418 0.03448 0.02693 -0.0642 0.9901 0.0834
-4.250 -0.3067 0.03179 0.02411 -0.0671 0.9856 0.0872
-4.000 -0.2694 0.02968 0.02148 -0.0693 0.9807 0.0879
-3.750 -0.2335 0.02812 0.01953 -0.0711 0.9751 0.0895
-3.250 -0.1620 0.02612 0.01693 -0.0744 0.9637 0.0982
-3.000 -0.1244 0.02522 0.01605 -0.0765 0.9587 0.1039
-2.750 -0.0922 0.02465 0.01535 -0.0773 0.9520 0.1119
-2.500 -0.0577 0.02394 0.01478 -0.0789 0.9460 0.1289
-2.250 -0.0209 0.02279 0.01413 -0.0809 0.9414 0.2000
-2.000 0.0065 0.02225 0.01420 -0.0814 0.9335 0.3456
-1.750 0.0445 0.02206 0.01437 -0.0835 0.9286 0.4494
-1.500 0.0661 0.02200 0.01463 -0.0825 0.9196 0.5359
-1.250 0.1030 0.02192 0.01483 -0.0839 0.9145 0.6443
-1.000 0.1230 0.02167 0.01495 -0.0819 0.9060 0.7530
-0.750 0.1801 0.02123 0.01471 -0.0874 0.9017 1.0000
-0.500 0.2116 0.02154 0.01477 -0.0887 0.8939 1.0000
-0.250 0.2492 0.02176 0.01477 -0.0908 0.8872 1.0000
0.000 0.2787 0.02208 0.01492 -0.0916 0.8791 1.0000
0.250 0.3158 0.02227 0.01497 -0.0935 0.8726 1.0000
0.500 0.3439 0.02259 0.01517 -0.0939 0.8643 1.0000
0.750 0.3811 0.02274 0.01522 -0.0957 0.8579 1.0000
1.000 0.4080 0.02308 0.01548 -0.0958 0.8494 1.0000
1.250 0.4457 0.02317 0.01551 -0.0976 0.8432 1.0000
1.500 0.4718 0.02351 0.01580 -0.0975 0.8345 1.0000
1.750 0.5102 0.02353 0.01579 -0.0993 0.8285 1.0000
2.000 0.5358 0.02388 0.01613 -0.0991 0.8197 1.0000
2.250 0.5748 0.02381 0.01606 -0.1009 0.8139 1.0000
2.500 0.6209 0.02354 0.01581 -0.1037 0.8100 1.0000
2.750 0.6408 0.02397 0.01627 -0.1025 0.7993 1.0000
3.000 0.6833 0.02374 0.01609 -0.1047 0.7946 1.0000
3.250 0.7072 0.02402 0.01641 -0.1040 0.7846 1.0000
3.500 0.7535 0.02353 0.01601 -0.1064 0.7808 1.0000
3.750 0.7735 0.02392 0.01646 -0.1051 0.7695 1.0000
4.000 0.7976 0.02419 0.01681 -0.1043 0.7594 1.0000
4.250 0.8416 0.02360 0.01634 -0.1062 0.7539 1.0000
4.500 0.8689 0.02350 0.01634 -0.1054 0.7424 1.0000
4.750 0.9087 0.02258 0.01553 -0.1059 0.7311 1.0000
5.000 0.9526 0.02146 0.01454 -0.1070 0.7200 1.0000
5.250 0.9861 0.02069 0.01387 -0.1064 0.7045 1.0000
5.500 1.0179 0.01974 0.01299 -0.1053 0.6838 1.0000
5.750 1.0509 0.01887 0.01216 -0.1045 0.6615 1.0000
6.000 1.0742 0.01861 0.01199 -0.1026 0.6387 1.0000
6.250 1.0976 0.01841 0.01186 -0.1008 0.6140 1.0000
6.500 1.1174 0.01829 0.01179 -0.0983 0.5833 1.0000
6.750 1.1346 0.01827 0.01178 -0.0954 0.5447 1.0000
7.000 1.1432 0.01851 0.01190 -0.0910 0.4866 1.0000
7.250 1.1403 0.01939 0.01223 -0.0849 0.3810 1.0000
7.500 1.1216 0.02156 0.01334 -0.0773 0.2432 1.0000
7.750 1.1073 0.02395 0.01497 -0.0710 0.1706 1.0000
8.000 1.1041 0.02592 0.01657 -0.0665 0.1384 1.0000
8.250 1.1087 0.02756 0.01809 -0.0632 0.1165 1.0000
8.500 1.1154 0.02922 0.01963 -0.0603 0.1015 1.0000
8.750 1.1271 0.03100 0.02135 -0.0581 0.0893 1.0000
9.000 1.1463 0.03292 0.02319 -0.0569 0.0788 1.0000
9.250 1.1861 0.03562 0.02575 -0.0585 0.0702 1.0000
9.500 1.2117 0.03749 0.02780 -0.0582 0.0639 1.0000
9.750 1.2662 0.04202 0.03241 -0.0626 0.0588 1.0000
10.000 1.2849 0.04452 0.03533 -0.0611 0.0570 1.0000
10.250 1.2980 0.04697 0.03816 -0.0590 0.0546 1.0000
10.500 1.3103 0.04965 0.04113 -0.0571 0.0526 1.0000
10.750 1.3188 0.05293 0.04479 -0.0548 0.0521 1.0000
11.000 1.3193 0.05641 0.04869 -0.0516 0.0521 1.0000
11.250 1.3117 0.05993 0.05262 -0.0476 0.0526 1.0000
11.500 1.2984 0.06357 0.05665 -0.0434 0.0533 1.0000
11.750 1.2818 0.06734 0.06076 -0.0396 0.0541 1.0000
12.000 1.2632 0.07136 0.06508 -0.0365 0.0549 1.0000
12.250 1.2436 0.07563 0.06961 -0.0341 0.0557 1.0000
12.500 1.2231 0.08022 0.07443 -0.0326 0.0565 1.0000
12.750 1.2018 0.08518 0.07960 -0.0318 0.0571 1.0000
13.000 1.1812 0.09062 0.08521 -0.0320 0.0578 1.0000
13.250 1.1649 0.09670 0.09141 -0.0327 0.0587 1.0000
13.500 1.1544 0.10184 0.09674 -0.0336 0.0607 1.0000
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Polar data table (+)
Polar graphs
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