AG46c -03f (ag46c03-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG46c -03f (ag46c03-il) Reynolds number: 500,000 Max Cl/Cd: 72.47 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag46c03-il-500000-n5.txt Download as CSV file: xf-ag46c03-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.5989 0.09924 0.09710 0.0257 1.0000 0.0094
-7.250 -0.5952 0.09514 0.09302 0.0234 1.0000 0.0094
-7.000 -0.5917 0.09097 0.08887 0.0208 1.0000 0.0094
-6.750 -0.5876 0.08665 0.08458 0.0175 1.0000 0.0094
-6.500 -0.5792 0.08167 0.07960 0.0122 1.0000 0.0094
-5.500 -0.5271 0.05351 0.05119 -0.0149 1.0000 0.0057
-5.250 -0.5062 0.04653 0.04401 -0.0199 1.0000 0.0056
-5.000 -0.4838 0.03901 0.03618 -0.0238 1.0000 0.0054
-4.750 -0.4609 0.02982 0.02647 -0.0263 1.0000 0.0052
-4.500 -0.4379 0.01988 0.01546 -0.0272 1.0000 0.0053
-4.250 -0.4119 0.01667 0.01164 -0.0270 1.0000 0.0056
-4.000 -0.3852 0.01512 0.00976 -0.0267 1.0000 0.0059
-3.750 -0.3588 0.01337 0.00772 -0.0265 1.0000 0.0063
-3.500 -0.3320 0.01249 0.00672 -0.0263 1.0000 0.0067
-3.250 -0.3050 0.01195 0.00612 -0.0261 1.0000 0.0072
-3.000 -0.2779 0.01151 0.00563 -0.0259 1.0000 0.0081
-2.750 -0.2423 0.01078 0.00477 -0.0275 0.9599 0.0087
-2.500 -0.2106 0.01023 0.00396 -0.0279 0.8664 0.0091
-2.250 -0.1875 0.01007 0.00340 -0.0265 0.7826 0.0094
-2.000 -0.1611 0.00962 0.00274 -0.0260 0.7517 0.0110
-1.750 -0.1339 0.00941 0.00239 -0.0257 0.7348 0.0131
-1.500 -0.1063 0.00918 0.00205 -0.0255 0.7229 0.0175
-1.250 -0.0787 0.00898 0.00183 -0.0253 0.7135 0.0283
-1.000 -0.0511 0.00879 0.00166 -0.0252 0.7053 0.0500
-0.750 -0.0232 0.00855 0.00152 -0.0252 0.6964 0.0852
-0.500 0.0046 0.00828 0.00139 -0.0252 0.6870 0.1355
-0.250 0.0324 0.00802 0.00130 -0.0252 0.6766 0.1966
0.000 0.0600 0.00770 0.00120 -0.0252 0.6649 0.2794
0.250 0.0873 0.00721 0.00113 -0.0253 0.6516 0.4197
0.500 0.1138 0.00667 0.00107 -0.0252 0.6364 0.5872
0.750 0.1386 0.00617 0.00105 -0.0244 0.6194 0.7473
1.000 0.1597 0.00582 0.00104 -0.0224 0.6007 0.8787
1.250 0.1946 0.00573 0.00096 -0.0235 0.5767 1.0000
1.500 0.2222 0.00584 0.00093 -0.0234 0.5523 1.0000
1.750 0.2499 0.00597 0.00092 -0.0232 0.5257 1.0000
2.000 0.2775 0.00612 0.00092 -0.0231 0.4975 1.0000
2.250 0.3051 0.00628 0.00095 -0.0230 0.4687 1.0000
2.500 0.3327 0.00646 0.00099 -0.0229 0.4391 1.0000
2.750 0.3603 0.00664 0.00104 -0.0229 0.4100 1.0000
3.000 0.3878 0.00684 0.00111 -0.0228 0.3809 1.0000
3.250 0.4154 0.00705 0.00120 -0.0228 0.3521 1.0000
3.500 0.4429 0.00726 0.00131 -0.0227 0.3247 1.0000
3.750 0.4704 0.00750 0.00143 -0.0227 0.2953 1.0000
4.000 0.4978 0.00774 0.00156 -0.0226 0.2684 1.0000
4.250 0.5251 0.00800 0.00171 -0.0226 0.2398 1.0000
4.500 0.5525 0.00826 0.00189 -0.0226 0.2161 1.0000
4.750 0.5797 0.00854 0.00208 -0.0225 0.1905 1.0000
5.000 0.6069 0.00883 0.00228 -0.0225 0.1691 1.0000
5.250 0.6341 0.00911 0.00250 -0.0224 0.1493 1.0000
5.500 0.6612 0.00941 0.00275 -0.0224 0.1311 1.0000
5.750 0.6883 0.00970 0.00300 -0.0223 0.1165 1.0000
6.000 0.7153 0.01003 0.00328 -0.0223 0.1015 1.0000
6.250 0.7423 0.01032 0.00356 -0.0222 0.0902 1.0000
6.500 0.7691 0.01065 0.00388 -0.0221 0.0784 1.0000
6.750 0.7959 0.01099 0.00421 -0.0220 0.0682 1.0000
7.000 0.8225 0.01135 0.00457 -0.0219 0.0584 1.0000
7.250 0.8489 0.01176 0.00495 -0.0218 0.0490 1.0000
7.500 0.8753 0.01217 0.00536 -0.0217 0.0408 1.0000
7.750 0.9015 0.01258 0.00582 -0.0216 0.0342 1.0000
8.000 0.9275 0.01308 0.00633 -0.0215 0.0281 1.0000
8.250 0.9534 0.01353 0.00682 -0.0213 0.0236 1.0000
8.500 0.9789 0.01411 0.00742 -0.0211 0.0191 1.0000
8.750 1.0045 0.01461 0.00801 -0.0209 0.0167 1.0000
9.000 1.0294 0.01528 0.00871 -0.0207 0.0139 1.0000
9.250 1.0543 0.01594 0.00950 -0.0205 0.0121 1.0000
9.500 1.0792 0.01654 0.01019 -0.0202 0.0106 1.0000
9.750 1.1033 0.01730 0.01102 -0.0200 0.0093 1.0000
10.000 1.1259 0.01842 0.01227 -0.0196 0.0081 1.0000
10.250 1.1494 0.01923 0.01323 -0.0193 0.0077 1.0000
10.500 1.1722 0.02015 0.01430 -0.0189 0.0071 1.0000
10.750 1.1947 0.02106 0.01533 -0.0185 0.0065 1.0000
11.000 1.2170 0.02195 0.01636 -0.0182 0.0059 1.0000
11.250 1.2366 0.02331 0.01785 -0.0178 0.0052 1.0000
11.500 1.2548 0.02487 0.01960 -0.0172 0.0049 1.0000
11.750 1.2735 0.02622 0.02116 -0.0167 0.0047 1.0000
12.000 1.2904 0.02777 0.02291 -0.0161 0.0045 1.0000
12.250 1.3055 0.02948 0.02483 -0.0155 0.0042 1.0000
12.500 1.3186 0.03134 0.02690 -0.0148 0.0040 1.0000
12.750 1.3293 0.03335 0.02912 -0.0142 0.0038 1.0000
13.000 1.3369 0.03554 0.03151 -0.0136 0.0037 1.0000
13.250 1.3391 0.03800 0.03417 -0.0130 0.0036 1.0000
13.500 1.3339 0.04108 0.03745 -0.0131 0.0035 1.0000
13.750 1.3257 0.04578 0.04236 -0.0164 0.0035 1.0000
14.000 1.3139 0.05191 0.04870 -0.0211 0.0034 1.0000
14.250 1.2971 0.05960 0.05659 -0.0270 0.0035 1.0000
14.500 1.2744 0.06886 0.06604 -0.0334 0.0035 1.0000
14.750 1.2455 0.07942 0.07677 -0.0400 0.0036 1.0000
15.000 1.2135 0.09051 0.08801 -0.0461 0.0037 1.0000
15.250 1.1798 0.10194 0.09957 -0.0520 0.0038 1.0000
15.500 1.1472 0.11328 0.11101 -0.0576 0.0039 1.0000
15.750 1.1157 0.12484 0.12266 -0.0632 0.0041 1.0000
16.000 1.0855 0.13686 0.13475 -0.0691 0.0042 1.0000
16.250 1.0543 0.14999 0.14795 -0.0754 0.0044 1.0000
16.500 1.0118 0.16815 0.16614 -0.0841 0.0047 1.0000
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Polar data table (+)
Polar graphs
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