NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-209 (naca63209-il) Reynolds number: 50,000 Max Cl/Cd: 32.06 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca63209-il-50000.txt Download as CSV file: xf-naca63209-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5079 0.10329 0.09637 0.0064 1.0000 0.3271
-8.500 -0.5089 0.10069 0.09383 0.0065 1.0000 0.3446
-8.250 -0.5107 0.09802 0.09124 0.0068 1.0000 0.3611
-7.750 -0.4950 0.09171 0.08499 0.0087 1.0000 0.4026
-7.500 -0.4697 0.08702 0.08026 0.0096 1.0000 0.4230
-7.250 -0.4628 0.08385 0.07710 0.0102 1.0000 0.4404
-7.000 -0.4594 0.08058 0.07388 0.0102 1.0000 0.4501
-6.750 -0.5599 0.06465 0.05826 -0.0248 1.0000 0.2287
-6.500 -0.5620 0.05330 0.04609 -0.0361 1.0000 0.1565
-6.250 -0.5495 0.04736 0.03921 -0.0383 1.0000 0.1332
-6.000 -0.5316 0.04293 0.03444 -0.0381 1.0000 0.1252
-5.750 -0.5118 0.03960 0.03020 -0.0377 1.0000 0.1199
-5.500 -0.4911 0.03672 0.02680 -0.0370 1.0000 0.1206
-5.250 -0.4690 0.03372 0.02346 -0.0362 1.0000 0.1211
-5.000 -0.4454 0.03109 0.02047 -0.0351 1.0000 0.1214
-4.750 -0.4218 0.02869 0.01793 -0.0340 1.0000 0.1238
-4.500 -0.3986 0.02693 0.01594 -0.0328 1.0000 0.1324
-4.250 -0.3757 0.02513 0.01417 -0.0313 1.0000 0.1423
-4.000 -0.3530 0.02354 0.01257 -0.0294 1.0000 0.1531
-3.750 -0.3325 0.02212 0.01122 -0.0277 1.0000 0.1775
-3.500 -0.3138 0.02025 0.00978 -0.0261 1.0000 0.2229
-3.250 -0.3203 0.01758 0.01002 -0.0174 1.0000 0.6681
-3.000 -0.1722 0.02101 0.01240 -0.0165 1.0000 0.9602
-2.750 -0.0732 0.01959 0.01025 -0.0315 1.0000 0.9939
-2.500 -0.0471 0.01891 0.00939 -0.0336 1.0000 1.0000
-2.250 -0.0415 0.01853 0.00897 -0.0318 1.0000 1.0000
-2.000 -0.0404 0.01824 0.00867 -0.0292 1.0000 1.0000
-1.750 -0.0449 0.01802 0.00845 -0.0258 1.0000 1.0000
-1.500 -0.0557 0.01785 0.00828 -0.0214 1.0000 1.0000
-1.250 -0.0703 0.01766 0.00810 -0.0165 1.0000 1.0000
-1.000 -0.0844 0.01745 0.00786 -0.0116 1.0000 1.0000
-0.750 -0.0891 0.01730 0.00760 -0.0082 1.0000 1.0000
-0.500 -0.0796 0.01731 0.00747 -0.0070 1.0000 1.0000
-0.250 -0.0634 0.01745 0.00746 -0.0067 1.0000 1.0000
0.000 -0.0446 0.01766 0.00753 -0.0068 1.0000 1.0000
0.250 -0.0249 0.01794 0.00769 -0.0069 1.0000 1.0000
0.500 -0.0047 0.01828 0.00791 -0.0072 1.0000 1.0000
0.750 0.0156 0.01867 0.00822 -0.0074 1.0000 1.0000
1.000 0.0358 0.01911 0.00858 -0.0077 1.0000 1.0000
1.250 0.0558 0.01960 0.00902 -0.0079 1.0000 1.0000
1.500 0.0757 0.02013 0.00952 -0.0082 1.0000 1.0000
1.750 0.0953 0.02071 0.01008 -0.0085 1.0000 1.0000
2.000 0.1148 0.02134 0.01070 -0.0088 1.0000 1.0000
2.250 0.1420 0.02218 0.01157 -0.0107 0.9960 1.0000
2.500 0.1905 0.02348 0.01296 -0.0164 0.9826 1.0000
2.750 0.2353 0.02464 0.01426 -0.0213 0.9680 1.0000
3.000 0.2782 0.02575 0.01551 -0.0257 0.9525 1.0000
3.250 0.3194 0.02682 0.01676 -0.0297 0.9361 1.0000
3.500 0.3617 0.02787 0.01806 -0.0335 0.9184 1.0000
3.750 0.4110 0.02891 0.01939 -0.0382 0.8993 1.0000
4.000 0.4486 0.02975 0.02051 -0.0406 0.8771 1.0000
4.250 0.4991 0.03036 0.02158 -0.0442 0.8513 1.0000
4.500 0.6241 0.02524 0.01753 -0.0465 0.7653 1.0000
4.750 0.6596 0.02132 0.01392 -0.0369 0.6814 1.0000
5.000 0.6544 0.02041 0.01132 -0.0232 0.3299 1.0000
5.250 0.6582 0.02424 0.01342 -0.0201 0.1914 1.0000
5.500 0.6819 0.02647 0.01542 -0.0187 0.1570 1.0000
5.750 0.7108 0.02870 0.01738 -0.0182 0.1349 1.0000
6.000 0.7436 0.03102 0.01982 -0.0178 0.1241 1.0000
6.250 0.7739 0.03366 0.02275 -0.0173 0.1177 1.0000
6.500 0.8006 0.03637 0.02553 -0.0169 0.1098 1.0000
6.750 0.8263 0.03980 0.02930 -0.0163 0.1081 1.0000
7.000 0.8497 0.04341 0.03335 -0.0154 0.1083 1.0000
7.250 0.8675 0.04667 0.03749 -0.0138 0.1112 1.0000
7.500 0.8800 0.05109 0.04272 -0.0126 0.1157 1.0000
7.750 0.8909 0.05565 0.04774 -0.0117 0.1185 1.0000
8.000 0.9018 0.06043 0.05281 -0.0112 0.1207 1.0000
8.250 0.8937 0.06601 0.05913 -0.0109 0.1307 1.0000
8.500 0.8813 0.07236 0.06591 -0.0119 0.1426 1.0000
8.750 0.7885 0.07070 0.06480 -0.0084 0.1520 1.0000
9.000 0.7327 0.07835 0.07247 -0.0124 0.1570 1.0000
9.250 0.6935 0.08862 0.08269 -0.0199 0.1694 1.0000
9.500 0.7208 0.11609 0.10951 -0.0542 0.3473 1.0000
9.750 0.7150 0.11968 0.11304 -0.0552 0.3368 1.0000
10.000 0.7410 0.12587 0.11935 -0.0551 0.3315 1.0000
10.250 0.7344 0.12875 0.12217 -0.0560 0.3187 1.0000
10.500 0.5987 0.12717 0.12101 -0.0455 0.3067 1.0000
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Polar data table (+)
Polar graphs
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