GOE 474 AIRFOIL (goe474-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 474 AIRFOIL (goe474-il) Reynolds number: 500,000 Max Cl/Cd: 101.65 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe474-il-500000.txt Download as CSV file: xf-goe474-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 474 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4448 0.08469 0.08243 -0.0275 1.0000 0.0228
-8.250 -0.4482 0.08136 0.07914 -0.0284 1.0000 0.0234
-7.250 -0.4675 0.06592 0.06380 -0.0358 1.0000 0.0263
-7.000 -0.4734 0.06189 0.05976 -0.0357 1.0000 0.0264
-6.750 -0.4933 0.02459 0.02071 -0.0547 0.9900 0.0167
-6.500 -0.4647 0.02126 0.01684 -0.0562 0.9866 0.0173
-6.250 -0.4328 0.01914 0.01432 -0.0576 0.9844 0.0182
-6.000 -0.4014 0.01780 0.01268 -0.0586 0.9815 0.0191
-5.750 -0.3738 0.01566 0.01020 -0.0590 0.9772 0.0204
-5.500 -0.3410 0.01483 0.00933 -0.0604 0.9744 0.0222
-5.250 -0.3067 0.01398 0.00834 -0.0618 0.9724 0.0239
-5.000 -0.2712 0.01327 0.00750 -0.0634 0.9708 0.0257
-4.750 -0.2426 0.01215 0.00622 -0.0636 0.9662 0.0278
-4.500 -0.2104 0.01138 0.00542 -0.0646 0.9627 0.0311
-4.250 -0.1756 0.01082 0.00478 -0.0660 0.9601 0.0342
-4.000 -0.1409 0.01020 0.00408 -0.0674 0.9577 0.0375
-3.750 -0.1106 0.00968 0.00354 -0.0679 0.9530 0.0428
-3.500 -0.0797 0.00934 0.00315 -0.0684 0.9478 0.0468
-3.250 -0.0474 0.00884 0.00276 -0.0693 0.9438 0.0689
-3.000 -0.0179 0.00868 0.00273 -0.0695 0.9374 0.1070
-2.750 0.0127 0.00862 0.00267 -0.0699 0.9313 0.1200
-2.500 0.0429 0.00854 0.00256 -0.0703 0.9254 0.1284
-2.250 0.0709 0.00849 0.00248 -0.0702 0.9179 0.1350
-2.000 0.0999 0.00838 0.00234 -0.0702 0.9115 0.1403
-1.750 0.1267 0.00828 0.00226 -0.0699 0.9032 0.1469
-1.500 0.1541 0.00823 0.00215 -0.0696 0.8945 0.1533
-1.250 0.1811 0.00808 0.00201 -0.0692 0.8849 0.1600
-1.000 0.2070 0.00802 0.00192 -0.0685 0.8741 0.1662
-0.750 0.2333 0.00790 0.00183 -0.0680 0.8647 0.1759
-0.500 0.2600 0.00781 0.00174 -0.0676 0.8555 0.1876
-0.250 0.2856 0.00770 0.00166 -0.0669 0.8437 0.2012
0.000 0.3111 0.00757 0.00159 -0.0663 0.8314 0.2240
0.250 0.3352 0.00721 0.00155 -0.0655 0.8197 0.3250
0.500 0.3788 0.00556 0.00169 -0.0687 0.8080 0.9679
0.750 0.4437 0.00561 0.00166 -0.0766 0.7918 0.9972
1.000 0.4759 0.00565 0.00162 -0.0774 0.7772 1.0000
1.250 0.4992 0.00570 0.00160 -0.0763 0.7605 1.0000
1.500 0.5229 0.00577 0.00160 -0.0752 0.7453 1.0000
1.750 0.5465 0.00584 0.00162 -0.0742 0.7293 1.0000
2.000 0.5701 0.00593 0.00165 -0.0731 0.7131 1.0000
2.250 0.5936 0.00602 0.00169 -0.0720 0.6947 1.0000
2.500 0.6165 0.00614 0.00174 -0.0708 0.6717 1.0000
2.750 0.6389 0.00630 0.00181 -0.0695 0.6436 1.0000
3.000 0.6607 0.00650 0.00189 -0.0681 0.6099 1.0000
3.250 0.6815 0.00677 0.00198 -0.0665 0.5608 1.0000
3.500 0.6974 0.00735 0.00215 -0.0640 0.4636 1.0000
3.750 0.7147 0.00798 0.00244 -0.0620 0.3909 1.0000
4.000 0.7345 0.00847 0.00270 -0.0605 0.3388 1.0000
4.250 0.7547 0.00894 0.00296 -0.0590 0.2879 1.0000
4.500 0.7744 0.00948 0.00324 -0.0576 0.2338 1.0000
4.750 0.7947 0.00998 0.00353 -0.0562 0.1941 1.0000
5.000 0.8163 0.01039 0.00384 -0.0550 0.1693 1.0000
5.250 0.8383 0.01077 0.00414 -0.0539 0.1495 1.0000
5.500 0.8609 0.01111 0.00443 -0.0529 0.1330 1.0000
5.750 0.8837 0.01144 0.00471 -0.0520 0.1200 1.0000
6.000 0.9064 0.01178 0.00503 -0.0510 0.1093 1.0000
6.250 0.9291 0.01213 0.00534 -0.0501 0.0985 1.0000
6.500 0.9522 0.01244 0.00565 -0.0493 0.0885 1.0000
6.750 0.9749 0.01279 0.00599 -0.0484 0.0771 1.0000
7.000 0.9966 0.01326 0.00639 -0.0473 0.0572 1.0000
7.250 1.0151 0.01408 0.00704 -0.0457 0.0345 1.0000
7.500 1.0343 0.01486 0.00783 -0.0442 0.0272 1.0000
7.750 1.0544 0.01552 0.00853 -0.0428 0.0237 1.0000
8.000 1.0711 0.01656 0.00965 -0.0409 0.0209 1.0000
8.250 1.0917 0.01715 0.01032 -0.0397 0.0195 1.0000
8.500 1.1113 0.01782 0.01106 -0.0383 0.0179 1.0000
8.750 1.1288 0.01870 0.01198 -0.0367 0.0165 1.0000
9.000 1.1392 0.02043 0.01384 -0.0340 0.0154 1.0000
9.250 1.1578 0.02119 0.01471 -0.0326 0.0149 1.0000
9.500 1.1745 0.02219 0.01582 -0.0309 0.0143 1.0000
9.750 1.1901 0.02331 0.01706 -0.0290 0.0138 1.0000
10.000 1.2051 0.02447 0.01836 -0.0272 0.0132 1.0000
10.250 1.2196 0.02553 0.01951 -0.0254 0.0126 1.0000
10.500 1.2323 0.02673 0.02081 -0.0234 0.0122 1.0000
10.750 1.2395 0.02842 0.02258 -0.0208 0.0115 1.0000
11.000 1.2403 0.03177 0.02620 -0.0176 0.0111 1.0000
11.250 1.2453 0.03308 0.02770 -0.0146 0.0109 1.0000
11.500 1.2478 0.03487 0.02968 -0.0117 0.0108 1.0000
11.750 1.2488 0.03662 0.03164 -0.0088 0.0106 1.0000
12.000 1.2472 0.03866 0.03389 -0.0061 0.0105 1.0000
12.250 1.2411 0.04129 0.03674 -0.0035 0.0104 1.0000
12.500 1.2338 0.04400 0.03967 -0.0014 0.0103 1.0000
12.750 1.2232 0.04723 0.04312 0.0002 0.0102 1.0000
13.000 1.2090 0.05113 0.04723 0.0011 0.0103 1.0000
13.250 1.1951 0.05522 0.05155 0.0012 0.0101 1.0000
13.500 1.1790 0.06000 0.05653 0.0003 0.0101 1.0000
13.750 1.1622 0.06542 0.06214 -0.0017 0.0100 1.0000
14.000 1.1408 0.07225 0.06914 -0.0051 0.0102 1.0000
14.250 1.1203 0.07988 0.07695 -0.0097 0.0102 1.0000
14.500 1.0947 0.08963 0.08688 -0.0161 0.0104 1.0000
14.750 1.0677 0.10065 0.09803 -0.0233 0.0107 1.0000
15.000 1.0398 0.11290 0.11044 -0.0312 0.0107 1.0000
15.250 1.0001 0.12818 0.12581 -0.0399 0.0110 1.0000
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Polar data table (+)
Polar graphs
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