RAF 32 AIRFOIL (raf32-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 32 AIRFOIL (raf32-il) Reynolds number: 100,000 Max Cl/Cd: 56.26 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf32-il-100000-n5.txt Download as CSV file: xf-raf32-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 32 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3172 0.09240 0.08743 -0.0703 0.9767 0.0411
-9.500 -0.3163 0.08713 0.08218 -0.0744 0.9704 0.0424
-9.250 -0.3204 0.08004 0.07511 -0.0808 0.9646 0.0438
-9.000 -0.3442 0.06950 0.06463 -0.0897 0.9551 0.0447
-8.750 -0.4095 0.04912 0.04385 -0.1103 0.9340 0.0427
-8.500 -0.4141 0.04231 0.03638 -0.1153 0.9246 0.0447
-8.250 -0.4028 0.03687 0.03003 -0.1187 0.9184 0.0475
-8.000 -0.3774 0.03586 0.02903 -0.1196 0.9143 0.0499
-7.750 -0.3601 0.03458 0.02752 -0.1192 0.9074 0.0530
-7.500 -0.3335 0.03205 0.02430 -0.1210 0.9037 0.0576
-7.250 -0.3016 0.03077 0.02298 -0.1229 0.9015 0.0615
-7.000 -0.2879 0.02997 0.02199 -0.1210 0.8930 0.0649
-6.750 -0.2585 0.02863 0.02015 -0.1221 0.8894 0.0700
-6.500 -0.2261 0.02754 0.01909 -0.1237 0.8871 0.0744
-6.250 -0.2059 0.02686 0.01822 -0.1227 0.8805 0.0786
-6.000 -0.1789 0.02604 0.01705 -0.1228 0.8756 0.0828
-5.750 -0.1476 0.02504 0.01609 -0.1240 0.8728 0.0873
-5.500 -0.1128 0.02423 0.01513 -0.1255 0.8706 0.0918
-5.250 -0.0942 0.02381 0.01453 -0.1240 0.8633 0.0956
-5.000 -0.0658 0.02308 0.01375 -0.1243 0.8589 0.0996
-4.750 -0.0325 0.02240 0.01302 -0.1255 0.8560 0.1037
-4.500 0.0024 0.02177 0.01228 -0.1269 0.8538 0.1085
-4.250 0.0188 0.02157 0.01201 -0.1249 0.8457 0.1130
-4.000 0.0486 0.02105 0.01150 -0.1254 0.8417 0.1207
-3.750 0.0824 0.02051 0.01092 -0.1266 0.8388 0.1306
-3.500 0.1101 0.02012 0.01053 -0.1267 0.8343 0.1434
-3.250 0.1312 0.01988 0.01036 -0.1256 0.8275 0.1623
-3.000 0.1629 0.01945 0.01006 -0.1265 0.8240 0.1993
-2.750 0.1978 0.01908 0.00976 -0.1278 0.8214 0.2446
-2.500 0.2162 0.01913 0.00984 -0.1262 0.8137 0.2757
-2.250 0.2452 0.01897 0.00971 -0.1264 0.8092 0.3064
-2.000 0.2790 0.01871 0.00947 -0.1275 0.8061 0.3355
-1.750 0.3042 0.01866 0.00946 -0.1271 0.8006 0.3646
-1.500 0.3278 0.01859 0.00952 -0.1263 0.7943 0.4038
-1.250 0.3592 0.01834 0.00942 -0.1269 0.7908 0.4510
-1.000 0.3937 0.01807 0.00922 -0.1279 0.7880 0.4914
-0.750 0.4081 0.01827 0.00951 -0.1255 0.7791 0.5216
-0.500 0.4402 0.01808 0.00937 -0.1260 0.7752 0.5630
-0.250 0.4753 0.01780 0.00915 -0.1271 0.7723 0.6073
0.000 0.4893 0.01800 0.00946 -0.1245 0.7633 0.6447
0.500 0.5469 0.01756 0.00927 -0.1241 0.7543 0.7531
0.750 0.5732 0.01742 0.00939 -0.1235 0.7475 0.8491
1.000 0.6200 0.01724 0.00918 -0.1273 0.7436 1.0000
1.250 0.6483 0.01734 0.00919 -0.1274 0.7384 1.0000
1.500 0.6696 0.01759 0.00938 -0.1263 0.7312 1.0000
1.750 0.7023 0.01758 0.00928 -0.1272 0.7270 1.0000
2.000 0.7243 0.01784 0.00951 -0.1262 0.7205 1.0000
2.250 0.7498 0.01799 0.00963 -0.1258 0.7144 1.0000
2.500 0.7838 0.01796 0.00955 -0.1268 0.7104 1.0000
2.750 0.8010 0.01834 0.00993 -0.1250 0.7026 1.0000
3.000 0.8296 0.01844 0.01000 -0.1251 0.6973 1.0000
3.250 0.8618 0.01846 0.01001 -0.1258 0.6928 1.0000
3.500 0.8783 0.01886 0.01045 -0.1239 0.6847 1.0000
3.750 0.9104 0.01888 0.01047 -0.1246 0.6798 1.0000
4.000 0.9312 0.01919 0.01082 -0.1234 0.6728 1.0000
4.250 0.9568 0.01937 0.01102 -0.1229 0.6663 1.0000
4.500 0.9908 0.01936 0.01103 -0.1239 0.6615 1.0000
4.750 1.0054 0.01979 0.01154 -0.1216 0.6523 1.0000
5.000 1.0393 0.01967 0.01142 -0.1224 0.6450 1.0000
5.250 1.0573 0.01989 0.01170 -0.1205 0.6337 1.0000
5.500 1.0781 0.02002 0.01187 -0.1190 0.6222 1.0000
5.750 1.1097 0.01997 0.01183 -0.1194 0.6135 1.0000
6.000 1.1239 0.02039 0.01236 -0.1170 0.6033 1.0000
6.250 1.1488 0.02056 0.01260 -0.1164 0.5947 1.0000
6.500 1.1691 0.02078 0.01289 -0.1149 0.5838 1.0000
6.750 1.1835 0.02109 0.01329 -0.1124 0.5711 1.0000
7.000 1.1979 0.02131 0.01356 -0.1098 0.5565 1.0000
7.250 1.2111 0.02157 0.01387 -0.1071 0.5406 1.0000
7.500 1.2239 0.02187 0.01421 -0.1043 0.5238 1.0000
7.750 1.2365 0.02223 0.01462 -0.1016 0.5065 1.0000
8.000 1.2494 0.02259 0.01498 -0.0990 0.4871 1.0000
8.250 1.2579 0.02315 0.01555 -0.0958 0.4649 1.0000
8.500 1.2683 0.02373 0.01609 -0.0930 0.4423 1.0000
8.750 1.2772 0.02444 0.01678 -0.0901 0.4188 1.0000
9.000 1.2847 0.02528 0.01759 -0.0872 0.3942 1.0000
9.250 1.2893 0.02631 0.01857 -0.0840 0.3657 1.0000
9.500 1.2899 0.02760 0.01973 -0.0806 0.3312 1.0000
9.750 1.2866 0.02923 0.02115 -0.0769 0.2923 1.0000
10.000 1.2812 0.03116 0.02284 -0.0734 0.2560 1.0000
10.250 1.2764 0.03323 0.02472 -0.0703 0.2242 1.0000
10.500 1.2738 0.03532 0.02667 -0.0677 0.1952 1.0000
10.750 1.2720 0.03746 0.02872 -0.0653 0.1661 1.0000
11.000 1.2689 0.03981 0.03093 -0.0631 0.1379 1.0000
11.250 1.2665 0.04222 0.03321 -0.0611 0.1161 1.0000
11.500 1.2647 0.04468 0.03559 -0.0594 0.1006 1.0000
11.750 1.2644 0.04710 0.03798 -0.0578 0.0895 1.0000
12.000 1.2643 0.04957 0.04046 -0.0564 0.0807 1.0000
12.250 1.2626 0.05229 0.04316 -0.0551 0.0734 1.0000
12.500 1.2644 0.05473 0.04572 -0.0541 0.0667 1.0000
12.750 1.2634 0.05754 0.04856 -0.0531 0.0614 1.0000
13.000 1.2650 0.06015 0.05130 -0.0522 0.0562 1.0000
13.250 1.2628 0.06322 0.05437 -0.0515 0.0525 1.0000
13.500 1.2665 0.06572 0.05705 -0.0508 0.0484 1.0000
13.750 1.2680 0.06854 0.05996 -0.0503 0.0449 1.0000
14.000 1.2670 0.07167 0.06311 -0.0500 0.0426 1.0000
14.250 1.2710 0.07425 0.06585 -0.0495 0.0401 1.0000
14.500 1.2744 0.07696 0.06870 -0.0491 0.0377 1.0000
14.750 1.2765 0.07988 0.07172 -0.0490 0.0357 1.0000
15.000 1.2781 0.08289 0.07481 -0.0490 0.0342 1.0000
15.250 1.2796 0.08587 0.07784 -0.0488 0.0327 1.0000
15.500 1.2844 0.08856 0.08071 -0.0486 0.0314 1.0000
15.750 1.2876 0.09153 0.08386 -0.0487 0.0300 1.0000
16.000 1.2896 0.09468 0.08717 -0.0489 0.0288 1.0000
16.250 1.2914 0.09789 0.09050 -0.0493 0.0278 1.0000
16.500 1.2927 0.10118 0.09391 -0.0498 0.0270 1.0000
16.750 1.2937 0.10450 0.09731 -0.0504 0.0263 1.0000
17.000 1.2952 0.10775 0.10063 -0.0509 0.0256 1.0000
17.250 1.2929 0.11186 0.10496 -0.0520 0.0250 1.0000
17.500 1.2872 0.11665 0.11001 -0.0537 0.0244 1.0000
17.750 1.2805 0.12172 0.11532 -0.0557 0.0239 1.0000
18.000 1.2721 0.12719 0.12102 -0.0581 0.0234 1.0000
18.250 1.2624 0.13306 0.12713 -0.0611 0.0231 1.0000
18.500 1.2507 0.13952 0.13381 -0.0645 0.0228 1.0000
18.750 1.2365 0.14677 0.14128 -0.0688 0.0227 1.0000
19.000 1.2186 0.15526 0.15000 -0.0741 0.0227 1.0000
19.250 1.1940 0.16615 0.16112 -0.0812 0.0228 1.0000
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