GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.7 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe417a-il-1000000.txt Download as CSV file: xf-goe417a-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417A (GEW. PLATTE) 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2270 0.10037 0.09874 -0.0390 0.9921 0.0129
-9.500 -0.2178 0.09702 0.09539 -0.0411 0.9907 0.0129
-9.250 -0.2088 0.09372 0.09210 -0.0435 0.9894 0.0130
-9.000 -0.1995 0.08932 0.08770 -0.0451 0.9882 0.0131
-8.750 -0.1887 0.08578 0.08415 -0.0469 0.9872 0.0131
-8.500 -0.1771 0.08256 0.08093 -0.0489 0.9863 0.0133
-8.250 -0.2617 0.09513 0.09343 -0.0420 0.9879 0.0131
-8.000 -0.2459 0.09204 0.09033 -0.0451 0.9863 0.0133
-7.750 -0.2290 0.08916 0.08745 -0.0487 0.9849 0.0135
-7.500 -0.2103 0.08620 0.08449 -0.0527 0.9837 0.0138
-7.250 -0.1947 0.08338 0.08166 -0.0555 0.9806 0.0142
-7.000 -0.1781 0.08057 0.07885 -0.0585 0.9774 0.0147
-6.750 -0.1562 0.07748 0.07575 -0.0628 0.9753 0.0152
-6.500 -0.1302 0.07425 0.07250 -0.0680 0.9737 0.0155
-6.250 -0.0996 0.07098 0.06920 -0.0745 0.9724 0.0156
-6.000 -0.0660 0.06760 0.06579 -0.0817 0.9714 0.0156
-5.750 -0.0294 0.06420 0.06234 -0.0895 0.9706 0.0157
-5.250 0.0117 0.05795 0.05606 -0.0947 0.9635 0.0158
-5.000 0.0371 0.05489 0.05298 -0.0979 0.9618 0.0159
-4.750 0.0678 0.05210 0.05016 -0.1023 0.9604 0.0161
-4.500 0.1004 0.04948 0.04752 -0.1068 0.9589 0.0164
-4.250 0.1343 0.04685 0.04485 -0.1114 0.9572 0.0168
-4.000 0.1671 0.04436 0.04231 -0.1155 0.9556 0.0175
-3.750 0.1876 0.04246 0.04038 -0.1160 0.9489 0.0182
-3.500 0.2246 0.04034 0.03817 -0.1198 0.9450 0.0185
-3.250 0.2600 0.03816 0.03591 -0.1233 0.9416 0.0186
-3.000 0.2848 0.03638 0.03406 -0.1240 0.9361 0.0186
-2.750 0.3133 0.03450 0.03209 -0.1252 0.9306 0.0186
-2.000 0.3850 0.02821 0.02560 -0.1262 0.9124 0.0188
-1.750 0.4049 0.02663 0.02399 -0.1258 0.9056 0.0191
-1.500 0.4286 0.02525 0.02255 -0.1256 0.8979 0.0193
-1.250 0.4522 0.02397 0.02121 -0.1252 0.8887 0.0198
-1.000 0.4775 0.02268 0.01982 -0.1249 0.8778 0.0206
-0.750 0.5042 0.02161 0.01862 -0.1242 0.8652 0.0216
-0.500 0.5314 0.02069 0.01755 -0.1233 0.8481 0.0218
-0.250 0.5551 0.01977 0.01642 -0.1219 0.8159 0.0219
0.000 0.5732 0.01903 0.01536 -0.1195 0.7641 0.0219
0.250 0.5919 0.01828 0.01437 -0.1173 0.7300 0.0219
0.500 0.6122 0.01748 0.01338 -0.1155 0.7054 0.0219
0.750 0.6302 0.01597 0.01166 -0.1134 0.6824 0.0222
1.000 0.6495 0.01523 0.01080 -0.1119 0.6586 0.0224
1.250 0.6695 0.01466 0.01008 -0.1103 0.6323 0.0227
1.500 0.6893 0.01419 0.00942 -0.1085 0.6006 0.0232
1.750 0.7100 0.01373 0.00878 -0.1067 0.5727 0.0241
2.000 0.7347 0.01370 0.00850 -0.1048 0.5497 0.0258
2.250 0.7557 0.01332 0.00791 -0.1030 0.5234 0.0258
5.750 1.0418 0.01289 0.00478 -0.0813 0.0408 0.0346
6.000 1.0614 0.01306 0.00493 -0.0795 0.0343 0.0332
6.250 1.0821 0.01324 0.00511 -0.0780 0.0315 0.0335
6.500 1.1010 0.01358 0.00547 -0.0762 0.0277 0.0346
6.750 1.1214 0.01383 0.00575 -0.0746 0.0261 0.0365
7.000 1.1415 0.01407 0.00601 -0.0731 0.0246 0.0395
7.250 1.1610 0.01437 0.00631 -0.0714 0.0229 0.0431
7.500 1.1766 0.01488 0.00699 -0.0690 0.0208 0.1548
7.750 1.3638 0.01573 0.00908 -0.1068 0.0170 1.0000
8.000 1.3771 0.01657 0.00999 -0.1040 0.0160 1.0000
8.250 1.3957 0.01694 0.01038 -0.1022 0.0156 1.0000
8.500 1.4131 0.01738 0.01086 -0.1003 0.0151 1.0000
8.750 1.4297 0.01786 0.01137 -0.0982 0.0145 1.0000
9.000 1.4457 0.01836 0.01192 -0.0960 0.0140 1.0000
9.250 1.4610 0.01887 0.01246 -0.0937 0.0135 1.0000
9.500 1.4746 0.01948 0.01310 -0.0911 0.0131 1.0000
9.750 1.4808 0.02056 0.01426 -0.0871 0.0126 1.0000
10.000 1.4797 0.02180 0.01560 -0.0818 0.0123 1.0000
10.250 1.4893 0.02229 0.01616 -0.0784 0.0121 1.0000
10.500 1.4998 0.02276 0.01668 -0.0753 0.0118 1.0000
10.750 1.5073 0.02351 0.01752 -0.0718 0.0116 1.0000
11.000 1.5175 0.02409 0.01815 -0.0688 0.0112 1.0000
11.250 1.5273 0.02473 0.01886 -0.0659 0.0109 1.0000
11.500 1.5340 0.02565 0.01986 -0.0626 0.0106 1.0000
11.750 1.5439 0.02630 0.02055 -0.0599 0.0103 1.0000
12.000 1.5492 0.02738 0.02172 -0.0567 0.0102 1.0000
12.250 1.5554 0.02838 0.02279 -0.0537 0.0100 1.0000
12.500 1.5602 0.02954 0.02402 -0.0507 0.0099 1.0000
12.750 1.5615 0.03104 0.02560 -0.0474 0.0096 1.0000
13.000 1.5561 0.03338 0.02809 -0.0436 0.0094 1.0000
13.250 1.5490 0.03613 0.03103 -0.0399 0.0092 1.0000
13.500 1.5526 0.03753 0.03254 -0.0375 0.0091 1.0000
13.750 1.5554 0.03905 0.03418 -0.0353 0.0090 1.0000
14.000 1.5527 0.04137 0.03664 -0.0328 0.0089 1.0000
14.250 1.5506 0.04362 0.03903 -0.0307 0.0088 1.0000
14.500 1.5476 0.04608 0.04163 -0.0289 0.0087 1.0000
14.750 1.5439 0.04871 0.04440 -0.0275 0.0086 1.0000
15.000 1.5367 0.05195 0.04779 -0.0262 0.0086 1.0000
15.250 1.5275 0.05562 0.05162 -0.0254 0.0085 1.0000
15.500 1.5210 0.05905 0.05518 -0.0251 0.0083 1.0000
15.750 1.5065 0.06384 0.06015 -0.0252 0.0084 1.0000
16.000 1.4902 0.06920 0.06571 -0.0259 0.0083 1.0000
16.250 1.4798 0.07390 0.07054 -0.0270 0.0082 1.0000
16.500 1.4693 0.07888 0.07564 -0.0285 0.0081 1.0000
16.750 1.4491 0.08574 0.08268 -0.0309 0.0081 1.0000
17.000 1.4323 0.09227 0.08936 -0.0336 0.0080 1.0000
17.250 1.4026 0.10161 0.09891 -0.0377 0.0081 1.0000
17.500 1.3868 0.10873 0.10616 -0.0413 0.0081 1.0000
17.750 1.3653 0.11735 0.11493 -0.0458 0.0081 1.0000
18.000 1.3271 0.13057 0.12837 -0.0533 0.0082 1.0000
18.250 1.2825 0.14663 0.14466 -0.0628 0.0084 1.0000
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Polar data table (+)
Polar graphs
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