GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Reynolds number: 200,000 Max Cl/Cd: 83.56 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe332-il-200000.txt Download as CSV file: xf-goe332-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 332 (PFALZ 61) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1384 0.09674 0.09333 -0.0673 0.9731 0.0496
-8.250 -0.1271 0.09335 0.08994 -0.0785 0.9609 0.0519
-8.000 -0.1128 0.08835 0.08494 -0.0891 0.9482 0.0525
-7.750 -0.0886 0.08415 0.08072 -0.0864 0.9474 0.0533
-7.500 -0.0680 0.08089 0.07745 -0.0877 0.9389 0.0544
-7.250 -0.0438 0.07732 0.07385 -0.0921 0.9327 0.0564
-7.000 -0.0233 0.07371 0.07020 -0.0984 0.9208 0.0594
-6.750 0.0056 0.06738 0.06373 -0.1171 0.9062 0.0622
-6.500 0.0240 0.06450 0.06084 -0.1154 0.8985 0.0631
-6.250 0.0449 0.06188 0.05817 -0.1162 0.8890 0.0645
-6.000 0.0653 0.05918 0.05540 -0.1189 0.8774 0.0667
-5.750 0.1034 0.05358 0.04940 -0.1345 0.8647 0.0729
-5.500 0.1192 0.05103 0.04685 -0.1331 0.8560 0.0739
-5.250 0.1356 0.04933 0.04514 -0.1321 0.8456 0.0756
-5.000 0.1759 0.04630 0.04153 -0.1414 0.8365 0.0848
-4.750 0.1907 0.04316 0.03850 -0.1405 0.8271 0.0859
-4.500 0.2108 0.04129 0.03660 -0.1403 0.8195 0.0875
-4.250 0.2474 0.04107 0.03578 -0.1440 0.8102 0.0977
-4.000 0.2657 0.03673 0.03152 -0.1446 0.8037 0.0995
-3.750 0.2857 0.03500 0.02982 -0.1442 0.7952 0.1014
-3.500 0.3175 0.03428 0.02875 -0.1456 0.7888 0.1113
-3.250 0.3390 0.03152 0.02591 -0.1461 0.7810 0.1152
-3.000 0.3634 0.03010 0.02445 -0.1462 0.7743 0.1191
-2.750 0.4043 0.02289 0.01577 -0.1480 0.7693 0.0729
-2.500 0.4299 0.02120 0.01396 -0.1479 0.7619 0.0700
-2.250 0.4590 0.01950 0.01189 -0.1480 0.7563 0.0675
-2.000 0.4858 0.01845 0.01059 -0.1476 0.7494 0.0673
-1.750 0.5136 0.01773 0.00967 -0.1474 0.7427 0.0687
-1.500 0.5424 0.01701 0.00874 -0.1473 0.7371 0.0692
-1.250 0.5684 0.01644 0.00809 -0.1468 0.7294 0.0700
-1.000 0.5969 0.01595 0.00748 -0.1466 0.7235 0.0715
-0.750 0.6230 0.01550 0.00702 -0.1462 0.7166 0.0735
-0.500 0.6501 0.01518 0.00673 -0.1459 0.7100 0.0779
-0.250 0.6788 0.01501 0.00649 -0.1459 0.7046 0.0846
0.000 0.7043 0.01479 0.00637 -0.1454 0.6974 0.0948
0.250 0.7327 0.01450 0.00620 -0.1454 0.6915 0.1338
0.500 0.7592 0.01430 0.00616 -0.1452 0.6852 0.2013
0.750 0.7855 0.01403 0.00615 -0.1451 0.6784 0.2775
1.000 0.8118 0.01256 0.00615 -0.1443 0.6733 1.0000
1.250 0.8367 0.01272 0.00623 -0.1436 0.6659 1.0000
1.500 0.8644 0.01283 0.00619 -0.1435 0.6595 1.0000
1.750 0.8909 0.01300 0.00625 -0.1432 0.6529 1.0000
2.000 0.9172 0.01314 0.00631 -0.1428 0.6457 1.0000
2.250 0.9458 0.01330 0.00632 -0.1429 0.6399 1.0000
2.500 0.9699 0.01346 0.00648 -0.1421 0.6316 1.0000
2.750 0.9980 0.01359 0.00649 -0.1421 0.6251 1.0000
3.000 1.0225 0.01378 0.00668 -0.1415 0.6171 1.0000
3.250 1.0496 0.01392 0.00674 -0.1413 0.6101 1.0000
3.500 1.0747 0.01412 0.00692 -0.1407 0.6023 1.0000
3.750 1.1009 0.01426 0.00701 -0.1404 0.5944 1.0000
4.000 1.1259 0.01445 0.00718 -0.1398 0.5862 1.0000
4.250 1.1516 0.01460 0.00730 -0.1394 0.5781 1.0000
4.500 1.1763 0.01480 0.00750 -0.1388 0.5698 1.0000
4.750 1.2017 0.01495 0.00761 -0.1384 0.5612 1.0000
5.000 1.2254 0.01515 0.00783 -0.1376 0.5519 1.0000
5.250 1.2511 0.01532 0.00794 -0.1372 0.5437 1.0000
5.500 1.2735 0.01553 0.00820 -0.1362 0.5335 1.0000
5.750 1.2977 0.01571 0.00833 -0.1355 0.5239 1.0000
6.000 1.3200 0.01587 0.00849 -0.1345 0.5129 1.0000
6.250 1.3413 0.01608 0.00873 -0.1333 0.5013 1.0000
6.500 1.3640 0.01633 0.00894 -0.1324 0.4911 1.0000
6.750 1.3862 0.01659 0.00918 -0.1314 0.4811 1.0000
7.000 1.4072 0.01690 0.00954 -0.1303 0.4706 1.0000
7.250 1.4297 0.01724 0.00983 -0.1294 0.4615 1.0000
7.500 1.4501 0.01758 0.01022 -0.1282 0.4516 1.0000
7.750 1.4713 0.01797 0.01063 -0.1271 0.4426 1.0000
8.000 1.4922 0.01836 0.01100 -0.1261 0.4337 1.0000
8.250 1.5110 0.01876 0.01148 -0.1246 0.4241 1.0000
8.500 1.5305 0.01919 0.01186 -0.1233 0.4144 1.0000
8.750 1.5455 0.01959 0.01232 -0.1211 0.4030 1.0000
9.000 1.5591 0.02004 0.01280 -0.1188 0.3912 1.0000
9.250 1.5715 0.02051 0.01328 -0.1162 0.3801 1.0000
9.500 1.5831 0.02103 0.01378 -0.1136 0.3698 1.0000
9.750 1.5933 0.02158 0.01442 -0.1108 0.3593 1.0000
10.000 1.6037 0.02220 0.01508 -0.1081 0.3491 1.0000
10.250 1.6122 0.02291 0.01579 -0.1053 0.3382 1.0000
10.500 1.6201 0.02366 0.01664 -0.1025 0.3268 1.0000
10.750 1.6284 0.02450 0.01753 -0.0999 0.3165 1.0000
11.000 1.6346 0.02549 0.01851 -0.0972 0.3061 1.0000
11.250 1.6407 0.02652 0.01967 -0.0947 0.2941 1.0000
11.500 1.6446 0.02777 0.02098 -0.0922 0.2807 1.0000
11.750 1.6475 0.02920 0.02246 -0.0897 0.2668 1.0000
12.000 1.6495 0.03082 0.02412 -0.0874 0.2521 1.0000
12.250 1.6490 0.03274 0.02605 -0.0852 0.2355 1.0000
12.500 1.6435 0.03520 0.02847 -0.0829 0.2157 1.0000
12.750 1.6361 0.03798 0.03119 -0.0807 0.1932 1.0000
13.000 1.6238 0.04136 0.03448 -0.0785 0.1717 1.0000
13.250 1.6086 0.04523 0.03823 -0.0766 0.1474 1.0000
13.500 1.5919 0.04948 0.04235 -0.0749 0.1187 1.0000
13.750 1.5712 0.05436 0.04706 -0.0735 0.0927 1.0000
14.000 1.5521 0.05928 0.05189 -0.0724 0.0756 1.0000
14.250 1.5370 0.06396 0.05654 -0.0716 0.0589 1.0000
14.500 1.5232 0.06861 0.06116 -0.0712 0.0491 1.0000
14.750 1.5110 0.07324 0.06580 -0.0709 0.0445 1.0000
15.000 1.5007 0.07776 0.07041 -0.0709 0.0419 1.0000
15.250 1.4894 0.08253 0.07526 -0.0710 0.0401 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 332 (PFALZ 61) AIRFOIL (goe332-il)