GOE 432 AIRFOIL (goe432-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 432 AIRFOIL (goe432-il) Reynolds number: 500,000 Max Cl/Cd: 94.79 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe432-il-500000.txt Download as CSV file: xf-goe432-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3775 0.08576 0.08366 -0.0178 1.0000 0.0203
-7.250 -0.3893 0.08396 0.08191 -0.0157 1.0000 0.0205
-7.000 -0.3953 0.08062 0.07862 -0.0184 1.0000 0.0213
-6.750 -0.3943 0.07676 0.07477 -0.0223 1.0000 0.0216
-6.500 -0.3704 0.07121 0.06917 -0.0302 0.9979 0.0217
-6.250 -0.3523 0.06586 0.06382 -0.0343 0.9952 0.0224
-6.000 -0.3246 0.06231 0.06023 -0.0390 0.9922 0.0229
-5.750 -0.2919 0.05787 0.05574 -0.0458 0.9883 0.0238
-5.500 -0.2510 0.05210 0.04985 -0.0550 0.9851 0.0255
-5.250 -0.1984 0.04264 0.04000 -0.0669 0.9803 0.0276
-5.000 -0.1740 0.02884 0.02559 -0.0735 0.9746 0.0209
-4.750 -0.1422 0.01947 0.01511 -0.0766 0.9716 0.0213
-4.500 -0.1142 0.01577 0.01077 -0.0771 0.9673 0.0225
-4.250 -0.0815 0.01515 0.01008 -0.0781 0.9629 0.0237
-4.000 -0.0453 0.01420 0.00895 -0.0797 0.9602 0.0255
-3.750 -0.0075 0.01321 0.00771 -0.0815 0.9583 0.0281
-3.500 0.0328 0.01250 0.00698 -0.0841 0.9565 0.0308
-3.250 0.0615 0.01198 0.00639 -0.0838 0.9483 0.0334
-3.000 0.0979 0.01108 0.00537 -0.0853 0.9433 0.0371
-2.750 0.1262 0.01078 0.00508 -0.0851 0.9342 0.0405
-2.500 0.1598 0.01040 0.00465 -0.0859 0.9272 0.0440
-2.250 0.1859 0.00972 0.00391 -0.0852 0.9143 0.0476
-2.000 0.2146 0.00929 0.00348 -0.0851 0.8997 0.0513
-1.750 0.2444 0.00900 0.00313 -0.0851 0.8814 0.0551
-1.500 0.2747 0.00876 0.00278 -0.0852 0.8565 0.0573
-1.250 0.3021 0.00835 0.00223 -0.0847 0.8244 0.0621
-1.000 0.3279 0.00827 0.00199 -0.0839 0.7893 0.0661
-0.750 0.3524 0.00829 0.00182 -0.0829 0.7518 0.0701
-0.500 0.3760 0.00828 0.00165 -0.0817 0.7096 0.0777
-0.250 0.3991 0.00835 0.00155 -0.0805 0.6628 0.0904
0.000 0.4204 0.00806 0.00155 -0.0792 0.6167 0.2496
0.250 0.4418 0.00782 0.00160 -0.0780 0.5793 0.4139
0.500 0.5020 0.00671 0.00171 -0.0852 0.5461 1.0000
0.750 0.5260 0.00690 0.00175 -0.0843 0.5269 1.0000
1.000 0.5504 0.00708 0.00179 -0.0834 0.5093 1.0000
1.250 0.5751 0.00724 0.00184 -0.0826 0.4942 1.0000
1.500 0.5999 0.00739 0.00189 -0.0818 0.4807 1.0000
1.750 0.6247 0.00754 0.00196 -0.0811 0.4680 1.0000
2.000 0.6499 0.00767 0.00202 -0.0804 0.4552 1.0000
2.250 0.6751 0.00781 0.00209 -0.0797 0.4426 1.0000
2.500 0.7001 0.00796 0.00217 -0.0790 0.4288 1.0000
2.750 0.7251 0.00811 0.00226 -0.0783 0.4142 1.0000
3.000 0.7500 0.00827 0.00235 -0.0776 0.3994 1.0000
3.250 0.7750 0.00844 0.00245 -0.0769 0.3856 1.0000
3.500 0.7998 0.00862 0.00256 -0.0763 0.3715 1.0000
3.750 0.8247 0.00880 0.00270 -0.0756 0.3570 1.0000
4.000 0.8495 0.00900 0.00284 -0.0749 0.3423 1.0000
4.250 0.8740 0.00922 0.00299 -0.0742 0.3248 1.0000
4.500 0.8980 0.00948 0.00316 -0.0734 0.3019 1.0000
4.750 0.9216 0.00980 0.00336 -0.0726 0.2716 1.0000
5.000 0.9444 0.01022 0.00360 -0.0717 0.2355 1.0000
5.250 0.9673 0.01063 0.00387 -0.0708 0.2112 1.0000
5.500 0.9908 0.01098 0.00417 -0.0700 0.1994 1.0000
5.750 1.0141 0.01134 0.00448 -0.0691 0.1919 1.0000
6.000 1.0383 0.01161 0.00477 -0.0684 0.1872 1.0000
6.250 1.0618 0.01194 0.00510 -0.0676 0.1826 1.0000
6.500 1.0844 0.01236 0.00550 -0.0667 0.1779 1.0000
6.750 1.1088 0.01260 0.00582 -0.0660 0.1749 1.0000
7.000 1.1323 0.01292 0.00617 -0.0652 0.1698 1.0000
7.250 1.1537 0.01343 0.00664 -0.0642 0.1632 1.0000
7.500 1.1787 0.01358 0.00689 -0.0637 0.1570 1.0000
7.750 1.2001 0.01406 0.00733 -0.0627 0.1487 1.0000
8.000 1.2255 0.01415 0.00753 -0.0623 0.1433 1.0000
8.250 1.2484 0.01448 0.00785 -0.0615 0.1362 1.0000
8.500 1.2729 0.01465 0.00811 -0.0609 0.1281 1.0000
8.750 1.2963 0.01493 0.00839 -0.0602 0.1177 1.0000
9.000 1.3185 0.01530 0.00870 -0.0594 0.1010 1.0000
9.250 1.3372 0.01598 0.00925 -0.0581 0.0816 1.0000
9.500 1.3499 0.01719 0.01022 -0.0559 0.0449 1.0000
9.750 1.3594 0.01866 0.01153 -0.0532 0.0258 1.0000
10.000 1.3749 0.01953 0.01248 -0.0513 0.0218 1.0000
10.250 1.3857 0.02072 0.01375 -0.0487 0.0190 1.0000
10.500 1.4006 0.02149 0.01462 -0.0467 0.0177 1.0000
10.750 1.4124 0.02234 0.01556 -0.0443 0.0165 1.0000
11.000 1.4193 0.02336 0.01667 -0.0412 0.0154 1.0000
11.250 1.4191 0.02479 0.01821 -0.0372 0.0146 1.0000
11.500 1.4221 0.02607 0.01961 -0.0340 0.0140 1.0000
11.750 1.4271 0.02726 0.02092 -0.0312 0.0136 1.0000
12.000 1.4299 0.02865 0.02243 -0.0284 0.0132 1.0000
12.250 1.4324 0.03015 0.02403 -0.0259 0.0127 1.0000
12.500 1.4322 0.03194 0.02594 -0.0236 0.0124 1.0000
12.750 1.4309 0.03395 0.02807 -0.0216 0.0121 1.0000
13.000 1.4280 0.03630 0.03053 -0.0200 0.0118 1.0000
13.250 1.4238 0.03900 0.03333 -0.0189 0.0115 1.0000
13.500 1.4176 0.04215 0.03660 -0.0183 0.0113 1.0000
13.750 1.4074 0.04606 0.04064 -0.0182 0.0110 1.0000
14.000 1.3963 0.05037 0.04508 -0.0187 0.0108 1.0000
14.250 1.3837 0.05509 0.04994 -0.0193 0.0107 1.0000
14.500 1.3794 0.05905 0.05405 -0.0205 0.0105 1.0000
14.750 1.3755 0.06309 0.05823 -0.0219 0.0103 1.0000
15.000 1.3701 0.06742 0.06269 -0.0235 0.0102 1.0000
15.250 1.3623 0.07219 0.06759 -0.0252 0.0100 1.0000
15.500 1.3541 0.07703 0.07256 -0.0269 0.0100 1.0000
15.750 1.3470 0.08195 0.07761 -0.0290 0.0098 1.0000
16.000 1.3382 0.08720 0.08299 -0.0312 0.0097 1.0000
16.250 1.3293 0.09262 0.08854 -0.0336 0.0096 1.0000
16.500 1.3197 0.09824 0.09429 -0.0361 0.0096 1.0000
16.750 1.3110 0.10393 0.10011 -0.0389 0.0095 1.0000
17.000 1.3012 0.10992 0.10623 -0.0417 0.0094 1.0000
17.250 1.2916 0.11609 0.11252 -0.0450 0.0093 1.0000
17.500 1.2808 0.12256 0.11913 -0.0484 0.0093 1.0000
17.750 1.2711 0.12907 0.12576 -0.0520 0.0092 1.0000
18.000 1.2612 0.13573 0.13255 -0.0558 0.0091 1.0000
18.250 1.2511 0.14259 0.13953 -0.0598 0.0091 1.0000
18.500 1.2387 0.15019 0.14727 -0.0644 0.0091 1.0000
18.750 1.2245 0.15857 0.15580 -0.0695 0.0092 1.0000
19.000 1.2116 0.16687 0.16424 -0.0748 0.0092 1.0000
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