NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Reynolds number: 100,000 Max Cl/Cd: 31.85 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc0864c-il-100000-n5.txt Download as CSV file: xf-rc0864c-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC08-64C AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5539 0.09436 0.08923 -0.0133 1.0000 0.0593
-8.250 -0.5549 0.09028 0.08520 -0.0161 1.0000 0.0607
-8.000 -0.5599 0.08590 0.08087 -0.0200 1.0000 0.0622
-7.750 -0.4960 0.06926 0.06452 -0.0308 1.0000 0.0676
-7.500 -0.4939 0.06538 0.06066 -0.0300 1.0000 0.0685
-7.250 -0.4953 0.06147 0.05674 -0.0297 1.0000 0.0694
-6.000 -0.5340 0.04935 0.04320 -0.0252 1.0000 0.0322
-5.750 -0.5235 0.04440 0.03768 -0.0227 1.0000 0.0261
-5.500 -0.5122 0.04154 0.03469 -0.0211 1.0000 0.0251
-5.250 -0.4996 0.03854 0.03142 -0.0191 1.0000 0.0238
-5.000 -0.4854 0.03516 0.02758 -0.0168 1.0000 0.0221
-4.750 -0.4677 0.03253 0.02430 -0.0142 1.0000 0.0205
-4.500 -0.4503 0.03032 0.02185 -0.0126 1.0000 0.0201
-4.250 -0.4315 0.02831 0.01956 -0.0109 1.0000 0.0197
-4.000 -0.4113 0.02648 0.01742 -0.0094 1.0000 0.0193
-3.750 -0.3900 0.02493 0.01556 -0.0079 1.0000 0.0195
-3.500 -0.3679 0.02362 0.01398 -0.0065 1.0000 0.0202
-3.250 -0.3452 0.02256 0.01265 -0.0052 1.0000 0.0207
-3.000 -0.3226 0.02122 0.01122 -0.0042 1.0000 0.0211
-2.750 -0.2999 0.02015 0.01008 -0.0031 1.0000 0.0211
-2.500 -0.2777 0.01919 0.00910 -0.0020 1.0000 0.0213
-2.250 -0.2558 0.01838 0.00827 -0.0010 1.0000 0.0216
-2.000 -0.2339 0.01772 0.00756 0.0001 1.0000 0.0222
-1.750 -0.2029 0.01713 0.00690 -0.0007 0.9968 0.0230
-1.500 -0.1673 0.01666 0.00633 -0.0025 0.9917 0.0246
-1.250 -0.1310 0.01624 0.00585 -0.0043 0.9866 0.0286
-1.000 -0.0960 0.01590 0.00548 -0.0058 0.9802 0.0339
-0.750 -0.0765 0.01274 0.00567 -0.0040 0.9791 0.7954
-0.500 0.0100 0.01299 0.00598 -0.0141 0.9899 1.0000
-0.250 0.0493 0.01304 0.00588 -0.0168 0.9822 1.0000
0.000 0.0900 0.01308 0.00582 -0.0198 0.9751 1.0000
0.250 0.1277 0.01310 0.00578 -0.0221 0.9658 1.0000
0.500 0.1665 0.01312 0.00578 -0.0246 0.9572 1.0000
0.750 0.2068 0.01312 0.00579 -0.0273 0.9489 1.0000
1.000 0.2427 0.01309 0.00581 -0.0290 0.9367 1.0000
1.250 0.2937 0.01256 0.00532 -0.0322 0.8963 1.0000
1.500 0.3257 0.01238 0.00518 -0.0323 0.8667 1.0000
1.750 0.3552 0.01214 0.00487 -0.0312 0.8119 1.0000
2.000 0.3792 0.01211 0.00451 -0.0288 0.7085 1.0000
2.250 0.3997 0.01255 0.00437 -0.0263 0.5711 1.0000
2.500 0.4104 0.01447 0.00459 -0.0233 0.2360 1.0000
2.750 0.4253 0.01630 0.00523 -0.0216 0.0338 1.0000
3.000 0.4472 0.01681 0.00574 -0.0204 0.0277 1.0000
3.250 0.4686 0.01735 0.00632 -0.0191 0.0245 1.0000
3.500 0.4900 0.01794 0.00698 -0.0178 0.0233 1.0000
3.750 0.5111 0.01855 0.00771 -0.0164 0.0225 1.0000
4.000 0.5315 0.01926 0.00854 -0.0149 0.0219 1.0000
4.250 0.5513 0.02008 0.00944 -0.0134 0.0214 1.0000
4.500 0.5709 0.02100 0.01043 -0.0118 0.0210 1.0000
4.750 0.5909 0.02205 0.01153 -0.0102 0.0207 1.0000
5.000 0.6118 0.02319 0.01273 -0.0089 0.0202 1.0000
5.250 0.6330 0.02443 0.01401 -0.0077 0.0193 1.0000
5.500 0.6544 0.02617 0.01575 -0.0067 0.0185 1.0000
5.750 0.6771 0.02750 0.01735 -0.0055 0.0180 1.0000
6.000 0.6992 0.02921 0.01928 -0.0043 0.0179 1.0000
6.250 0.7205 0.03113 0.02146 -0.0031 0.0180 1.0000
6.500 0.7404 0.03324 0.02386 -0.0018 0.0181 1.0000
6.750 0.7587 0.03556 0.02649 -0.0003 0.0183 1.0000
7.000 0.7754 0.03812 0.02932 0.0011 0.0184 1.0000
7.250 0.7914 0.04037 0.03198 0.0028 0.0188 1.0000
7.500 0.8014 0.04395 0.03633 0.0057 0.0198 1.0000
7.750 0.8082 0.04783 0.04070 0.0080 0.0207 1.0000
8.000 0.8124 0.05169 0.04495 0.0100 0.0214 1.0000
8.250 0.8143 0.05547 0.04904 0.0117 0.0221 1.0000
8.500 0.8140 0.05920 0.05301 0.0133 0.0226 1.0000
8.750 0.8117 0.06285 0.05685 0.0146 0.0230 1.0000
9.000 0.8083 0.06640 0.06052 0.0156 0.0234 1.0000
9.250 0.8072 0.06979 0.06395 0.0165 0.0237 1.0000
9.500 0.7635 0.07762 0.07225 0.0150 0.0258 1.0000
9.750 0.7426 0.08540 0.08012 0.0094 0.0265 1.0000
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Polar data table (+)
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