GOE 432 AIRFOIL (goe432-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 432 AIRFOIL (goe432-il) Reynolds number: 500,000 Max Cl/Cd: 88.3 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe432-il-500000-n5.txt Download as CSV file: xf-goe432-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 432 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3516 0.09695 0.09472 -0.0223 1.0000 0.0073
-8.500 -0.3526 0.09444 0.09224 -0.0219 1.0000 0.0070
-8.250 -0.3561 0.09177 0.08960 -0.0213 1.0000 0.0071
-8.000 -0.3520 0.08823 0.08609 -0.0232 0.9989 0.0071
-7.750 -0.3397 0.08360 0.08147 -0.0282 0.9957 0.0071
-6.750 -0.2803 0.02095 0.01719 -0.0915 0.9680 0.0079
-6.500 -0.2513 0.01722 0.01281 -0.0935 0.9659 0.0083
-6.250 -0.2223 0.01583 0.01119 -0.0942 0.9630 0.0087
-6.000 -0.1960 0.01488 0.01005 -0.0940 0.9585 0.0091
-5.750 -0.1651 0.01401 0.00901 -0.0948 0.9552 0.0098
-5.500 -0.1323 0.01323 0.00805 -0.0958 0.9524 0.0107
-5.250 -0.1065 0.01251 0.00715 -0.0953 0.9459 0.0112
-5.000 -0.0767 0.01160 0.00607 -0.0956 0.9392 0.0122
-4.750 -0.0488 0.01109 0.00548 -0.0954 0.9299 0.0133
-4.500 -0.0176 0.01060 0.00488 -0.0959 0.9220 0.0147
-4.250 0.0087 0.01018 0.00438 -0.0954 0.9112 0.0163
-4.000 0.0378 0.00988 0.00405 -0.0954 0.8997 0.0191
-3.750 0.0687 0.00958 0.00364 -0.0958 0.8817 0.0220
-3.500 0.0996 0.00942 0.00341 -0.0961 0.8563 0.0258
-3.250 0.1283 0.00940 0.00320 -0.0959 0.8258 0.0293
-3.000 0.1544 0.00932 0.00298 -0.0953 0.7948 0.0322
-2.750 0.1801 0.00939 0.00291 -0.0946 0.7654 0.0352
-2.500 0.2052 0.00942 0.00276 -0.0938 0.7351 0.0376
-2.250 0.2299 0.00940 0.00258 -0.0929 0.7037 0.0395
-2.000 0.2539 0.00935 0.00238 -0.0919 0.6661 0.0426
-1.750 0.2772 0.00943 0.00223 -0.0909 0.6183 0.0446
-1.500 0.3007 0.00953 0.00209 -0.0898 0.5736 0.0463
-1.250 0.3254 0.00958 0.00198 -0.0890 0.5445 0.0480
-1.000 0.3509 0.00962 0.00188 -0.0884 0.5249 0.0497
-0.750 0.3767 0.00959 0.00177 -0.0879 0.5087 0.0528
-0.500 0.4028 0.00957 0.00168 -0.0874 0.4952 0.0565
-0.250 0.4289 0.00957 0.00163 -0.0870 0.4813 0.0605
0.250 0.4814 0.00957 0.00158 -0.0861 0.4563 0.0820
0.500 0.5071 0.00948 0.00158 -0.0856 0.4445 0.1386
0.750 0.5323 0.00930 0.00166 -0.0852 0.4319 0.2559
1.000 0.5578 0.00920 0.00172 -0.0847 0.4191 0.3338
1.250 0.5818 0.00890 0.00181 -0.0841 0.4075 0.4989
1.750 0.6567 0.00812 0.00198 -0.0883 0.3808 1.0000
2.000 0.6819 0.00828 0.00205 -0.0877 0.3669 1.0000
2.250 0.7070 0.00845 0.00213 -0.0870 0.3539 1.0000
2.500 0.7321 0.00862 0.00222 -0.0864 0.3410 1.0000
2.750 0.7572 0.00881 0.00232 -0.0858 0.3271 1.0000
3.000 0.7820 0.00901 0.00244 -0.0851 0.3112 1.0000
3.250 0.8068 0.00923 0.00257 -0.0845 0.2938 1.0000
3.500 0.8316 0.00945 0.00270 -0.0838 0.2755 1.0000
3.750 0.8558 0.00973 0.00286 -0.0831 0.2503 1.0000
4.000 0.8784 0.01018 0.00309 -0.0822 0.2085 1.0000
4.250 0.9016 0.01057 0.00335 -0.0814 0.1863 1.0000
4.500 0.9262 0.01083 0.00356 -0.0808 0.1790 1.0000
4.750 0.9508 0.01107 0.00378 -0.0801 0.1741 1.0000
5.000 0.9752 0.01133 0.00403 -0.0795 0.1698 1.0000
5.250 1.0002 0.01153 0.00425 -0.0789 0.1674 1.0000
5.500 1.0249 0.01175 0.00449 -0.0783 0.1644 1.0000
5.750 1.0492 0.01200 0.00477 -0.0777 0.1612 1.0000
6.000 1.0733 0.01227 0.00505 -0.0770 0.1582 1.0000
6.250 1.0971 0.01257 0.00536 -0.0763 0.1555 1.0000
6.500 1.1214 0.01280 0.00564 -0.0756 0.1536 1.0000
6.750 1.1459 0.01301 0.00593 -0.0750 0.1519 1.0000
7.000 1.1700 0.01325 0.00622 -0.0744 0.1494 1.0000
7.250 1.1938 0.01352 0.00653 -0.0737 0.1455 1.0000
7.500 1.2165 0.01388 0.00688 -0.0729 0.1394 1.0000
7.750 1.2410 0.01407 0.00714 -0.0723 0.1319 1.0000
8.000 1.2642 0.01436 0.00742 -0.0716 0.1216 1.0000
8.250 1.2860 0.01478 0.00773 -0.0707 0.1008 1.0000
8.500 1.3059 0.01537 0.00822 -0.0695 0.0845 1.0000
8.750 1.3257 0.01593 0.00876 -0.0683 0.0735 1.0000
9.000 1.3437 0.01664 0.00940 -0.0669 0.0552 1.0000
9.250 1.3544 0.01795 0.01049 -0.0644 0.0252 1.0000
9.500 1.3687 0.01891 0.01141 -0.0624 0.0150 1.0000
9.750 1.3856 0.01960 0.01217 -0.0607 0.0118 1.0000
10.000 1.4013 0.02034 0.01297 -0.0589 0.0102 1.0000
10.250 1.4153 0.02113 0.01384 -0.0569 0.0089 1.0000
10.500 1.4289 0.02181 0.01462 -0.0547 0.0082 1.0000
10.750 1.4406 0.02257 0.01547 -0.0523 0.0076 1.0000
11.000 1.4503 0.02346 0.01644 -0.0497 0.0070 1.0000
11.250 1.4579 0.02448 0.01759 -0.0469 0.0066 1.0000
11.500 1.4653 0.02553 0.01874 -0.0442 0.0062 1.0000
11.750 1.4740 0.02651 0.01982 -0.0419 0.0059 1.0000
12.000 1.4801 0.02769 0.02111 -0.0395 0.0056 1.0000
12.250 1.4861 0.02891 0.02243 -0.0372 0.0053 1.0000
12.500 1.4904 0.03030 0.02393 -0.0350 0.0050 1.0000
12.750 1.4916 0.03203 0.02577 -0.0328 0.0049 1.0000
13.000 1.4905 0.03405 0.02791 -0.0309 0.0047 1.0000
13.250 1.4846 0.03669 0.03068 -0.0292 0.0045 1.0000
13.500 1.4802 0.03943 0.03355 -0.0281 0.0044 1.0000
13.750 1.4769 0.04230 0.03657 -0.0275 0.0043 1.0000
14.000 1.4730 0.04548 0.03991 -0.0274 0.0043 1.0000
14.250 1.4645 0.04952 0.04410 -0.0279 0.0043 1.0000
14.500 1.4573 0.05371 0.04843 -0.0289 0.0042 1.0000
14.750 1.4476 0.05856 0.05345 -0.0304 0.0041 1.0000
15.000 1.4372 0.06373 0.05876 -0.0323 0.0040 1.0000
15.250 1.4222 0.06975 0.06493 -0.0347 0.0040 1.0000
15.500 1.4098 0.07552 0.07084 -0.0370 0.0039 1.0000
15.750 1.3956 0.08169 0.07715 -0.0396 0.0039 1.0000
16.000 1.3794 0.08839 0.08398 -0.0425 0.0039 1.0000
16.250 1.3636 0.09516 0.09089 -0.0456 0.0039 1.0000
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Polar data table (+)
Polar graphs
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