RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 32 MOD AIRFOIL (raf32md-il) Reynolds number: 1,000,000 Max Cl/Cd: 144.39 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf32md-il-1000000.txt Download as CSV file: xf-raf32md-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2954 0.12105 0.11949 -0.0395 0.9995 0.0143
-12.000 -0.2888 0.11744 0.11588 -0.0416 0.9989 0.0149
-11.750 -0.7925 0.02710 0.02425 -0.1040 0.9879 0.0103
-11.500 -0.7664 0.02500 0.02198 -0.1070 0.9858 0.0107
-11.250 -0.7348 0.02432 0.02125 -0.1091 0.9848 0.0111
-11.000 -0.7030 0.02354 0.02040 -0.1112 0.9838 0.0114
-10.750 -0.6792 0.02243 0.01916 -0.1118 0.9801 0.0118
-10.500 -0.6519 0.02133 0.01791 -0.1131 0.9773 0.0122
-10.250 -0.6220 0.02029 0.01672 -0.1147 0.9754 0.0127
-10.000 -0.5904 0.01944 0.01572 -0.1164 0.9740 0.0131
-9.750 -0.5610 0.01759 0.01364 -0.1186 0.9727 0.0139
-9.500 -0.5262 0.01744 0.01350 -0.1204 0.9717 0.0144
-9.250 -0.4946 0.01720 0.01322 -0.1215 0.9696 0.0149
-9.000 -0.4686 0.01674 0.01269 -0.1215 0.9647 0.0155
-8.750 -0.4387 0.01615 0.01198 -0.1224 0.9614 0.0163
-8.500 -0.4074 0.01564 0.01136 -0.1235 0.9587 0.0168
-8.250 -0.3829 0.01432 0.00986 -0.1236 0.9536 0.0176
-8.000 -0.3565 0.01395 0.00947 -0.1236 0.9479 0.0183
-7.750 -0.3260 0.01381 0.00932 -0.1244 0.9440 0.0191
-7.500 -0.2997 0.01357 0.00901 -0.1243 0.9378 0.0199
-7.250 -0.2728 0.01321 0.00856 -0.1242 0.9318 0.0208
-7.000 -0.2449 0.01290 0.00817 -0.1243 0.9263 0.0215
-6.750 -0.2182 0.01288 0.00808 -0.1240 0.9194 0.0219
-6.500 -0.1953 0.01136 0.00643 -0.1236 0.9129 0.0235
-6.250 -0.1699 0.01106 0.00612 -0.1233 0.9057 0.0245
-6.000 -0.1429 0.01073 0.00571 -0.1232 0.8996 0.0254
-5.750 -0.1172 0.01038 0.00531 -0.1228 0.8926 0.0263
-5.500 -0.0904 0.01010 0.00496 -0.1226 0.8862 0.0272
-5.250 -0.0636 0.00994 0.00475 -0.1224 0.8796 0.0280
-5.000 -0.0366 0.00977 0.00452 -0.1222 0.8731 0.0284
-4.750 -0.0128 0.00892 0.00355 -0.1216 0.8665 0.0298
-4.500 0.0131 0.00856 0.00314 -0.1212 0.8597 0.0310
-4.250 0.0398 0.00832 0.00284 -0.1210 0.8537 0.0321
-4.000 0.0664 0.00809 0.00257 -0.1207 0.8471 0.0331
-3.750 0.0934 0.00792 0.00232 -0.1205 0.8410 0.0340
-3.500 0.1203 0.00774 0.00211 -0.1203 0.8346 0.0352
-3.250 0.1474 0.00762 0.00193 -0.1201 0.8283 0.0362
-3.000 0.1745 0.00748 0.00175 -0.1199 0.8222 0.0373
-2.750 0.2015 0.00734 0.00156 -0.1196 0.8156 0.0399
-2.500 0.2287 0.00722 0.00142 -0.1194 0.8095 0.0441
-2.250 0.2549 0.00692 0.00129 -0.1192 0.8028 0.0918
-1.750 0.3074 0.00642 0.00113 -0.1187 0.7895 0.2064
-1.500 0.3338 0.00624 0.00111 -0.1185 0.7827 0.2707
-1.250 0.3608 0.00615 0.00109 -0.1183 0.7758 0.3037
-1.000 0.3876 0.00608 0.00107 -0.1181 0.7685 0.3351
-0.750 0.4146 0.00601 0.00106 -0.1179 0.7611 0.3621
-0.500 0.4413 0.00595 0.00105 -0.1176 0.7533 0.3906
-0.250 0.4679 0.00585 0.00104 -0.1174 0.7454 0.4298
0.000 0.4933 0.00567 0.00109 -0.1170 0.7373 0.5233
0.250 0.5196 0.00558 0.00114 -0.1166 0.7285 0.5865
0.500 0.5456 0.00555 0.00118 -0.1162 0.7200 0.6263
0.750 0.5718 0.00551 0.00121 -0.1158 0.7106 0.6563
1.000 0.5977 0.00547 0.00125 -0.1153 0.7013 0.6897
1.250 0.6228 0.00544 0.00130 -0.1147 0.6918 0.7327
1.500 0.6462 0.00530 0.00136 -0.1136 0.6816 0.8101
1.750 0.6968 0.00506 0.00144 -0.1186 0.6680 1.0000
2.000 0.7220 0.00517 0.00149 -0.1180 0.6556 1.0000
2.250 0.7468 0.00528 0.00154 -0.1173 0.6413 1.0000
2.500 0.7712 0.00542 0.00161 -0.1166 0.6242 1.0000
2.750 0.7956 0.00557 0.00169 -0.1158 0.6075 1.0000
3.000 0.8202 0.00572 0.00177 -0.1151 0.5917 1.0000
3.250 0.8448 0.00587 0.00187 -0.1144 0.5759 1.0000
3.500 0.8693 0.00603 0.00197 -0.1137 0.5588 1.0000
3.750 0.8938 0.00619 0.00209 -0.1130 0.5415 1.0000
4.000 0.9175 0.00639 0.00221 -0.1122 0.5193 1.0000
4.250 0.9410 0.00662 0.00236 -0.1113 0.4963 1.0000
4.500 0.9634 0.00690 0.00253 -0.1103 0.4669 1.0000
4.750 0.9833 0.00733 0.00276 -0.1088 0.4209 1.0000
5.000 1.0011 0.00791 0.00306 -0.1069 0.3623 1.0000
5.250 1.0160 0.00869 0.00346 -0.1046 0.2881 1.0000
5.500 1.0301 0.00954 0.00394 -0.1022 0.2140 1.0000
5.750 1.0462 0.01026 0.00438 -0.1002 0.1612 1.0000
6.000 1.0628 0.01093 0.00481 -0.0983 0.1155 1.0000
6.250 1.0787 0.01163 0.00528 -0.0962 0.0750 1.0000
6.500 1.0981 0.01208 0.00565 -0.0947 0.0604 1.0000
6.750 1.1191 0.01242 0.00598 -0.0935 0.0537 1.0000
7.000 1.1395 0.01278 0.00633 -0.0922 0.0470 1.0000
7.250 1.1592 0.01316 0.00668 -0.0908 0.0405 1.0000
7.500 1.1782 0.01352 0.00702 -0.0893 0.0340 1.0000
7.750 1.1947 0.01396 0.00743 -0.0872 0.0272 1.0000
8.000 1.2101 0.01445 0.00789 -0.0850 0.0221 1.0000
8.250 1.2261 0.01491 0.00834 -0.0829 0.0194 1.0000
8.500 1.2407 0.01547 0.00892 -0.0806 0.0173 1.0000
8.750 1.2574 0.01591 0.00940 -0.0788 0.0161 1.0000
9.000 1.2726 0.01644 0.00995 -0.0767 0.0149 1.0000
9.250 1.2855 0.01711 0.01066 -0.0743 0.0139 1.0000
9.500 1.2973 0.01786 0.01147 -0.0718 0.0132 1.0000
9.750 1.3127 0.01840 0.01207 -0.0700 0.0126 1.0000
10.000 1.3261 0.01906 0.01279 -0.0679 0.0122 1.0000
10.250 1.3394 0.01975 0.01351 -0.0659 0.0116 1.0000
10.500 1.3520 0.02050 0.01432 -0.0638 0.0112 1.0000
10.750 1.3620 0.02143 0.01530 -0.0615 0.0107 1.0000
11.000 1.3646 0.02287 0.01684 -0.0583 0.0101 1.0000
11.250 1.3732 0.02397 0.01802 -0.0561 0.0099 1.0000
11.500 1.3861 0.02480 0.01890 -0.0545 0.0096 1.0000
11.750 1.3966 0.02581 0.01999 -0.0526 0.0094 1.0000
12.000 1.4070 0.02687 0.02112 -0.0509 0.0091 1.0000
12.250 1.4153 0.02811 0.02244 -0.0490 0.0089 1.0000
12.500 1.4239 0.02936 0.02376 -0.0473 0.0086 1.0000
12.750 1.4325 0.03065 0.02511 -0.0457 0.0083 1.0000
13.000 1.4393 0.03212 0.02665 -0.0441 0.0081 1.0000
13.250 1.4446 0.03376 0.02836 -0.0425 0.0079 1.0000
13.500 1.4482 0.03562 0.03029 -0.0409 0.0078 1.0000
13.750 1.4403 0.03866 0.03347 -0.0388 0.0074 1.0000
14.000 1.4350 0.04162 0.03657 -0.0370 0.0073 1.0000
14.250 1.4373 0.04385 0.03892 -0.0359 0.0073 1.0000
14.500 1.4435 0.04572 0.04088 -0.0352 0.0072 1.0000
14.750 1.4468 0.04798 0.04326 -0.0344 0.0071 1.0000
15.000 1.4481 0.05054 0.04593 -0.0338 0.0070 1.0000
15.250 1.4479 0.05335 0.04886 -0.0334 0.0069 1.0000
15.500 1.4469 0.05636 0.05199 -0.0331 0.0068 1.0000
15.750 1.4456 0.05953 0.05528 -0.0331 0.0067 1.0000
16.000 1.4436 0.06290 0.05876 -0.0333 0.0066 1.0000
16.250 1.4423 0.06627 0.06224 -0.0337 0.0065 1.0000
16.500 1.4373 0.07028 0.06638 -0.0344 0.0064 1.0000
16.750 1.4343 0.07417 0.07037 -0.0353 0.0062 1.0000
17.000 1.4248 0.07918 0.07553 -0.0366 0.0062 1.0000
17.250 1.4185 0.08384 0.08032 -0.0382 0.0061 1.0000
17.500 1.4110 0.08888 0.08547 -0.0401 0.0060 1.0000
17.750 1.4052 0.09380 0.09049 -0.0421 0.0059 1.0000
18.000 1.3917 0.10022 0.09707 -0.0449 0.0059 1.0000
18.250 1.3796 0.10662 0.10360 -0.0480 0.0059 1.0000
18.500 1.3679 0.11315 0.11025 -0.0513 0.0058 1.0000
18.750 1.3556 0.12001 0.11723 -0.0550 0.0058 1.0000
19.000 1.3384 0.12810 0.12548 -0.0595 0.0058 1.0000
19.250 1.3214 0.13638 0.13392 -0.0644 0.0058 1.0000
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