AG46c -03f (ag46c03-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG46c -03f (ag46c03-il) Reynolds number: 200,000 Max Cl/Cd: 55.55 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag46c03-il-200000-n5.txt Download as CSV file: xf-ag46c03-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG46c -03f
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4900 0.11938 0.11607 0.0190 1.0000 0.0217
-9.000 -0.4889 0.11564 0.11235 0.0177 1.0000 0.0218
-6.000 -0.5507 0.07257 0.06925 -0.0009 1.0000 0.0142
-5.750 -0.5402 0.06780 0.06445 -0.0046 1.0000 0.0134
-5.500 -0.5243 0.06221 0.05880 -0.0098 1.0000 0.0127
-5.250 -0.5054 0.05608 0.05253 -0.0150 1.0000 0.0121
-5.000 -0.4842 0.04940 0.04564 -0.0197 1.0000 0.0115
-4.750 -0.4609 0.04202 0.03793 -0.0236 1.0000 0.0109
-4.500 -0.4366 0.03449 0.02990 -0.0260 1.0000 0.0106
-4.250 -0.4118 0.02887 0.02370 -0.0271 1.0000 0.0106
-4.000 -0.3863 0.02568 0.02009 -0.0275 1.0000 0.0112
-3.750 -0.3599 0.02342 0.01742 -0.0275 1.0000 0.0130
-3.500 -0.3328 0.02087 0.01437 -0.0273 1.0000 0.0137
-3.250 -0.3057 0.01867 0.01174 -0.0270 1.0000 0.0139
-3.000 -0.2785 0.01696 0.00969 -0.0266 1.0000 0.0142
-2.750 -0.2515 0.01563 0.00814 -0.0262 1.0000 0.0145
-2.500 -0.2250 0.01403 0.00642 -0.0259 1.0000 0.0156
-2.250 -0.1982 0.01314 0.00549 -0.0256 1.0000 0.0171
-2.000 -0.1712 0.01254 0.00485 -0.0254 1.0000 0.0205
-1.750 -0.1442 0.01180 0.00407 -0.0252 1.0000 0.0253
-1.500 -0.1170 0.01128 0.00348 -0.0249 1.0000 0.0330
-1.250 -0.0899 0.01070 0.00301 -0.0248 1.0000 0.0544
-1.000 -0.0519 0.01010 0.00268 -0.0272 0.9558 0.1203
-0.750 -0.0144 0.00954 0.00244 -0.0293 0.8931 0.2254
-0.500 0.0136 0.00890 0.00223 -0.0293 0.8312 0.3927
-0.250 0.0346 0.00808 0.00215 -0.0276 0.7916 0.6403
0.000 0.0515 0.00757 0.00213 -0.0240 0.7659 0.8541
0.250 0.0913 0.00751 0.00196 -0.0258 0.7449 1.0000
0.500 0.1180 0.00765 0.00187 -0.0254 0.7282 1.0000
0.750 0.1449 0.00780 0.00183 -0.0250 0.7136 1.0000
1.000 0.1720 0.00795 0.00181 -0.0247 0.6997 1.0000
1.250 0.1994 0.00804 0.00180 -0.0245 0.6842 1.0000
1.500 0.2268 0.00813 0.00179 -0.0242 0.6678 1.0000
1.750 0.2542 0.00821 0.00179 -0.0240 0.6497 1.0000
2.000 0.2815 0.00830 0.00178 -0.0237 0.6295 1.0000
2.250 0.3087 0.00840 0.00179 -0.0234 0.6071 1.0000
2.500 0.3358 0.00852 0.00179 -0.0231 0.5821 1.0000
2.750 0.3628 0.00866 0.00181 -0.0228 0.5545 1.0000
3.000 0.3897 0.00883 0.00186 -0.0225 0.5245 1.0000
3.250 0.4166 0.00903 0.00192 -0.0223 0.4932 1.0000
3.500 0.4435 0.00926 0.00204 -0.0220 0.4605 1.0000
3.750 0.4703 0.00951 0.00215 -0.0218 0.4274 1.0000
4.000 0.4971 0.00978 0.00230 -0.0216 0.3937 1.0000
4.250 0.5239 0.01008 0.00247 -0.0214 0.3604 1.0000
4.500 0.5507 0.01040 0.00271 -0.0213 0.3267 1.0000
4.750 0.5773 0.01075 0.00294 -0.0212 0.2932 1.0000
5.000 0.6040 0.01112 0.00321 -0.0210 0.2609 1.0000
5.250 0.6305 0.01150 0.00350 -0.0209 0.2302 1.0000
5.500 0.6570 0.01192 0.00386 -0.0208 0.2021 1.0000
5.750 0.6834 0.01235 0.00422 -0.0207 0.1767 1.0000
6.000 0.7097 0.01280 0.00462 -0.0206 0.1548 1.0000
6.250 0.7360 0.01325 0.00505 -0.0205 0.1350 1.0000
6.500 0.7622 0.01372 0.00551 -0.0204 0.1186 1.0000
6.750 0.7882 0.01423 0.00603 -0.0203 0.1030 1.0000
7.000 0.8141 0.01475 0.00657 -0.0201 0.0896 1.0000
7.250 0.8399 0.01530 0.00715 -0.0199 0.0774 1.0000
7.500 0.8654 0.01588 0.00776 -0.0198 0.0658 1.0000
7.750 0.8908 0.01651 0.00846 -0.0195 0.0563 1.0000
8.000 0.9157 0.01723 0.00925 -0.0193 0.0472 1.0000
8.250 0.9401 0.01804 0.01011 -0.0191 0.0397 1.0000
8.500 0.9647 0.01881 0.01102 -0.0188 0.0336 1.0000
8.750 0.9877 0.01992 0.01217 -0.0184 0.0282 1.0000
9.000 1.0113 0.02088 0.01334 -0.0180 0.0250 1.0000
9.250 1.0343 0.02188 0.01444 -0.0177 0.0214 1.0000
9.500 1.0553 0.02335 0.01611 -0.0172 0.0188 1.0000
9.750 1.0764 0.02476 0.01775 -0.0166 0.0171 1.0000
10.000 1.0967 0.02628 0.01948 -0.0161 0.0156 1.0000
10.250 1.1164 0.02770 0.02106 -0.0156 0.0142 1.0000
10.500 1.1316 0.03002 0.02357 -0.0150 0.0128 1.0000
10.750 1.1491 0.03182 0.02569 -0.0144 0.0119 1.0000
11.000 1.1629 0.03424 0.02845 -0.0137 0.0112 1.0000
11.250 1.1738 0.03694 0.03148 -0.0130 0.0106 1.0000
11.500 1.1812 0.03985 0.03472 -0.0124 0.0101 1.0000
11.750 1.1844 0.04302 0.03820 -0.0119 0.0098 1.0000
12.000 1.1815 0.04643 0.04195 -0.0116 0.0096 1.0000
12.250 1.1715 0.05037 0.04614 -0.0124 0.0094 1.0000
12.500 1.1584 0.05583 0.05186 -0.0162 0.0094 1.0000
12.750 1.1419 0.06284 0.05912 -0.0217 0.0094 1.0000
13.000 1.1210 0.07171 0.06817 -0.0288 0.0095 1.0000
13.250 1.0939 0.08283 0.07950 -0.0371 0.0098 1.0000
13.500 1.0592 0.09632 0.09315 -0.0458 0.0103 1.0000
13.750 1.0186 0.11156 0.10845 -0.0543 0.0109 1.0000
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Polar data table (+)
Polar graphs
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